From 721164e6aecc0b7387f7d16decd420b3070a8b5c Mon Sep 17 00:00:00 2001 From: dzalkind <65573423+dzalkind@users.noreply.github.com> Date: Mon, 10 Jun 2024 09:32:10 -0600 Subject: [PATCH 1/6] Bug fixes and documentation updates (#345) * Set types on wrap functions * Update IEA-15 inputs * Update installation instructions -- draft * Change to new AF Coords * Fix IEA15 airfoils again * Try latest setup_fortran action * Add UAStart/End location writing * Try intel-classic compiler * Add developer docs about api changes * Try macos-latest in CI * trying to improve conda and pypi builds (#351) * trying to improve conda and pypi builds * adding wheel to cibuild prep * overkill on linux libraries * forgot a step * removing musl aarch64, but don't understand why it fails --------- Co-authored-by: Garrett Barter --- .github/workflows/CI_rosco-compile.yml | 6 +- .github/workflows/Publish_ROSCO.yml | 40 +- ...rds.txt => IEA-15-240-RWT_AF00_Coords.txt} | 78 +-- .../Airfoils/IEA-15-240-RWT_AF01_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF02_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF03_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF04_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF05_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF06_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF07_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF08_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF09_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF10_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF11_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF12_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF13_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF14_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF15_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF16_Coords.txt | 208 ++++++ .../Airfoils/IEA-15-240-RWT_AF17_Coords.txt | 208 ++++++ 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------ .../IEA-15-240-RWT_AeroDyn15_Polar_10.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_10_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_11.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_11_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_12.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_12_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_13.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_13_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_14.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_14_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_15.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_15_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_16.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_16_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_17.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_17_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_18.dat | 366 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| 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_27.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_27_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_28.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_28_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_29.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_29_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_30.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_30_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_31.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_31_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_32.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_32_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_33.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_33_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_34.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_34_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_35.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_35_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_36.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_36_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_37.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_37_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_38.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_38_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_39.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_39_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_40.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_40_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_41.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_41_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_42.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_42_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_43.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_43_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_44.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_44_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_45.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_45_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_46.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_46_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_47.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_47_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_48.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_48_Coords.txt | 208 ------ .../IEA-15-240-RWT_AeroDyn15_Polar_49.dat | 366 ++++++---- ...A-15-240-RWT_AeroDyn15_Polar_49_Coords.txt | 208 ------ .../IEA-15-240-RWT-UMaineSemi.fst | 2 +- .../IEA-15-240-RWT-UMaineSemi_ElastoDyn.dat | 48 +- .../IEA-15-240-RWT-UMaineSemi_HydroDyn.dat | 132 ++-- .../IEA-15-240-RWT-UMaineSemi_MoorDyn.dat | 8 +- .../IEA-15-240-RWT-UMaineSemi_ServoDyn.dat | 20 +- .../IEA-15-240-RWT_AeroDyn15.dat | 74 ++- .../IEA-15-240-RWT_AeroDyn15_blade.dat | 104 +-- .../IEA-15-240-RWT_BeamDyn.dat | 117 ++-- .../IEA-15-240-RWT_BeamDyn_blade.dat | 625 ++++++++++-------- .../IEA-15-240-RWT_ElastoDyn_blade.dat | 136 ++-- .../IEA-15-240-RWT_InflowFile.dat | 20 +- .../IEA-15-240-RWT_OLAF.fst | 71 ++ docs/source/how_to_contribute_code.rst | 10 + docs/source/install.rst | 20 +- pyproject.toml | 7 +- rosco/controller/src/Functions.f90 | 4 +- rosco/controller/src/ROSCO_IO.f90 | 14 +- .../controller/src/SysFiles/SysLLVMLinux.f90 | 190 ++++++ rosco/controller/src/SysFiles/SysLLVMWin.f90 | 184 ++++++ rosco/toolbox/ofTools/fast_io/FAST_writer.py | 4 + 171 files changed, 22508 insertions(+), 18090 deletions(-) rename Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/{IEA-15-240-RWT_AeroDyn15_Polar_00_Coords.txt => IEA-15-240-RWT_AF00_Coords.txt} (81%) create mode 100644 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Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_46_Coords.txt delete mode 100644 Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_47_Coords.txt delete mode 100644 Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_48_Coords.txt delete mode 100644 Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_49_Coords.txt create mode 100644 Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_OLAF.fst create mode 100644 rosco/controller/src/SysFiles/SysLLVMLinux.f90 create mode 100644 rosco/controller/src/SysFiles/SysLLVMWin.f90 diff --git a/.github/workflows/CI_rosco-compile.yml b/.github/workflows/CI_rosco-compile.yml index f5a1135c..e352cdc9 100644 --- a/.github/workflows/CI_rosco-compile.yml +++ b/.github/workflows/CI_rosco-compile.yml @@ -16,13 +16,15 @@ jobs: strategy: fail-fast: false #true matrix: - os: ["ubuntu-latest", "macOS-13", "windows-latest"] #mac-13 intel, mac-14 arm + os: ["ubuntu-latest", "macOS-latest", "windows-latest"] #mac-13 intel, mac-14 arm python-version: ["3.9", "3.10", "3.11", "3.12"] steps: - name: Setup GNU Fortran if: false == contains( matrix.os, 'windows') - uses: awvwgk/setup-fortran@v1 #modflowpy/install-intelfortran-action@v1 # + uses: fortran-lang/setup-fortran@v1.6 + # with: + # compiler: intel-classic - name: Install compiler if: false == contains( matrix.os, 'windows') diff --git a/.github/workflows/Publish_ROSCO.yml b/.github/workflows/Publish_ROSCO.yml index 0f5e5c96..2202c5fe 100644 --- a/.github/workflows/Publish_ROSCO.yml +++ b/.github/workflows/Publish_ROSCO.yml @@ -12,9 +12,15 @@ jobs: strategy: fail-fast: false matrix: - os: [ubuntu-latest, windows-latest, macos-13, macos-14] + os: [ubuntu-latest, windows-latest, macos-12, macos-13, macos-14] steps: + - name: Set up QEMU + if: runner.os == 'Linux' + uses: docker/setup-qemu-action@v3 + with: + platforms: all + - name: Setup GNU Fortran if: false == contains( matrix.os, 'windows') uses: awvwgk/setup-fortran@v1 @@ -51,16 +57,40 @@ jobs: - name: Checkout uses: actions/checkout@v4 - - name: Build wheels mac and linux - if: false == contains( matrix.os, 'windows') - uses: pypa/cibuildwheel@v2.17.0 + - name: Build wheels linux + if: contains( matrix.os, 'ubuntu') + uses: pypa/cibuildwheel@v2.18.1 + env: + CC: ${{ steps.install_cc.outputs.cc }} + CXX: ${{ steps.install_cc.outputs.cxx }} + + - name: Build wheels mac-12 + if: contains( matrix.os, 'macos-12') + uses: pypa/cibuildwheel@v2.18.1 + env: + CC: ${{ steps.install_cc.outputs.cc }} + CXX: ${{ steps.install_cc.outputs.cxx }} + CIBW_ENVIRONMENT_MACOS: MACOSX_DEPLOYMENT_TARGET="12.0" + + - name: Build wheels mac-13 + if: contains( matrix.os, 'macos-13') + uses: pypa/cibuildwheel@v2.18.1 + env: + CC: ${{ steps.install_cc.outputs.cc }} + CXX: ${{ steps.install_cc.outputs.cxx }} + CIBW_ENVIRONMENT_MACOS: MACOSX_DEPLOYMENT_TARGET="13.0" + + - name: Build wheels mac-14 + if: contains( matrix.os, 'macos-14') + uses: pypa/cibuildwheel@v2.18.1 env: CC: ${{ steps.install_cc.outputs.cc }} CXX: ${{ steps.install_cc.outputs.cxx }} + CIBW_ENVIRONMENT_MACOS: MACOSX_DEPLOYMENT_TARGET="14.0" - name: Build wheels windows if: contains( matrix.os, 'windows') - uses: pypa/cibuildwheel@v2.17.0 + uses: pypa/cibuildwheel@v2.18.1 - uses: actions/upload-artifact@v4 with: diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF00_Coords.txt similarity index 81% rename from Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00_Coords.txt rename to Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF00_Coords.txt index 47ed851a..c384a4c8 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00_Coords.txt +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF00_Coords.txt @@ -2,15 +2,15 @@ ! ......... x-y coordinates are next if NumCoords > 0 ............. ! x-y coordinate of airfoil reference ! x/c y/c - 0.504545 0. + 0.500000 0 ! coordinates of airfoil shape ! interpolation to 200 points ! x/c y/c - 1.00000000000000e+00 -5.22832942930268e-16 + 1.00000000000000e+00 -5.22829392626822e-16 9.99429683992583e-01 -2.22597407115582e-02 9.98063017832965e-01 -4.44580348954677e-02 9.95573914266674e-01 -6.65618134473914e-02 - 9.92086309749559e-01 -8.85198205325816e-02 + 9.92086309749560e-01 -8.85198205325816e-02 9.87686148675057e-01 -1.10275272231260e-01 9.82330525170640e-01 -1.31784370919739e-01 9.76011908335692e-01 -1.53006617635088e-01 @@ -30,7 +30,7 @@ 8.04073832217581e-01 -3.96914898117900e-01 7.87191529885653e-01 -4.09289340064311e-01 7.69897919101553e-01 -4.20894001702843e-01 - 7.52252341235159e-01 -4.31703640475795e-01 + 7.52252341235159e-01 -4.31703640475796e-01 7.34291349178558e-01 -4.41704116420428e-01 7.16044924955764e-01 -4.50916295010545e-01 6.97571640033109e-01 -4.59311192391506e-01 @@ -46,62 +46,62 @@ 5.08535950506088e-01 -4.99900147123151e-01 4.89992355470388e-01 -4.99865122336167e-01 4.71632114506831e-01 -4.99152990523336e-01 - 4.53492503744347e-01 -4.97865574847876e-01 + 4.53492503744348e-01 -4.97865574847876e-01 4.35593302897673e-01 -4.95849221396458e-01 4.17956065616942e-01 -4.93220204257438e-01 4.00609748442576e-01 -4.90034017714886e-01 3.83560931606009e-01 -4.86240654381211e-01 3.66843215733716e-01 -4.81953122075711e-01 3.50457316320503e-01 -4.77107036591688e-01 - 3.34434484008630e-01 -4.71801617147633e-01 + 3.34434484008630e-01 -4.71801617147634e-01 3.18774100329315e-01 -4.65997503105357e-01 3.03499623121295e-01 -4.59771833639973e-01 2.88611293565648e-01 -4.53111012774598e-01 2.74124386665666e-01 -4.46071472676040e-01 2.60041455523719e-01 -4.38653996586565e-01 - 2.46374872015917e-01 -4.30897288076141e-01 - 2.33123443938834e-01 -4.22812892154316e-01 - 2.20293777810423e-01 -4.14442160590302e-01 + 2.46374872015918e-01 -4.30897288076141e-01 + 2.33123443938833e-01 -4.22812892154316e-01 + 2.20293777810423e-01 -4.14442160590301e-01 2.07883282965331e-01 -4.05790731420267e-01 1.95902956391646e-01 -3.96897110059902e-01 1.84341253066628e-01 -3.87763028932806e-01 - 1.73213930954160e-01 -3.78432781857511e-01 + 1.73213930954161e-01 -3.78432781857511e-01 1.62499176129638e-01 -3.68901685535316e-01 - 1.52214602777260e-01 -3.59220819204806e-01 + 1.52214602777259e-01 -3.59220819204806e-01 1.42331759398971e-01 -3.49381794975500e-01 1.32872111539190e-01 -3.39428678290192e-01 1.23806439629760e-01 -3.29359452404754e-01 1.15147623386077e-01 -3.19202364510091e-01 - 1.06887208802748e-01 -3.08971834769008e-01 + 1.06887208802748e-01 -3.08971834769009e-01 9.90071115215634e-02 -2.98675440643128e-01 - 9.15234043853439e-02 -2.88346537239591e-01 + 9.15234043853440e-02 -2.88346537239591e-01 8.43970428172224e-02 -2.77979120522002e-01 7.76464790199521e-02 -2.67604205770439e-01 - 7.12479082120209e-02 -2.57229212452774e-01 + 7.12479082120208e-02 -2.57229212452774e-01 6.51878662973747e-02 -2.46861090082763e-01 - 5.94874721274202e-02 -2.36524433012696e-01 + 5.94874721274203e-02 -2.36524433012697e-01 5.41002464180900e-02 -2.26213901273871e-01 4.90378786701877e-02 -2.15949074862572e-01 - 4.43003497573338e-02 -2.05745246473815e-01 - 3.98423597346806e-02 -1.95597654428208e-01 + 4.43003497573340e-02 -2.05745246473815e-01 + 3.98423597346805e-02 -1.95597654428208e-01 3.56899752436130e-02 -1.85525503303304e-01 - 3.18292350050658e-02 -1.75535988753057e-01 - 2.82200072057899e-02 -1.65626936732462e-01 - 2.48925247792699e-02 -1.55815221490220e-01 - 2.18286683030034e-02 -1.46105621815703e-01 - 1.89846947131331e-02 -1.36495337998243e-01 + 3.18292350050659e-02 -1.75535988753057e-01 + 2.82200072057900e-02 -1.65626936732462e-01 + 2.48925247792698e-02 -1.55815221490219e-01 + 2.18286683030035e-02 -1.46105621815703e-01 + 1.89846947131332e-02 -1.36495337998243e-01 1.63921917020335e-02 -1.26998300581103e-01 1.40446346341990e-02 -1.17620770590061e-01 - 1.18798249846349e-02 -1.08356847039079e-01 - 9.93094518736223e-03 -9.92166214620375e-02 + 1.18798249846349e-02 -1.08356847039080e-01 + 9.93094518736226e-03 -9.92166214620377e-02 8.21940795734749e-03 -9.02084101294225e-02 6.65838622137879e-03 -8.13254351098410e-02 5.26774192850643e-03 -7.25722234042700e-02 4.09515753852961e-03 -6.39564017315716e-02 - 3.09878859713640e-03 -5.54780130210999e-02 + 3.09878859713642e-03 -5.54780130211000e-02 2.19660773551101e-03 -4.71320046999757e-02 1.46264176301869e-03 -3.89244052604170e-02 - 9.64484608297914e-04 -3.08606101713945e-02 + 9.64484608297922e-04 -3.08606101713947e-02 5.99373867982851e-04 -2.29362359459691e-02 2.90086645599082e-04 -1.51487658773967e-02 7.80707788302466e-05 -7.50222207649338e-03 @@ -119,29 +119,29 @@ 8.18368429859057e-03 9.00120990085718e-02 9.88361416849065e-03 9.89814202866229e-02 1.18176401547236e-02 1.08079023747493e-01 - 1.39661993216829e-02 1.17296891553284e-01 + 1.39661993216830e-02 1.17296891553284e-01 1.62951420791042e-02 1.26624818507885e-01 1.88631937781153e-02 1.36068234819796e-01 2.16807137532775e-02 1.45621741073938e-01 2.47159162958630e-02 1.55271505652796e-01 - 2.80064400105862e-02 1.65019126539152e-01 + 2.80064400105864e-02 1.65019126539152e-01 3.15762558914965e-02 1.74861450420233e-01 3.53948396168776e-02 1.84781748500356e-01 3.94949825480075e-02 1.94780451150684e-01 4.38979282781582e-02 2.04852826049369e-01 4.85758075737765e-02 2.14979335736815e-01 - 5.35679916138119e-02 2.25163248876704e-01 + 5.35679916138118e-02 2.25163248876704e-01 5.88818211488708e-02 2.35392575398327e-01 - 6.45001629027312e-02 2.45645861854957e-01 + 6.45001629027313e-02 2.45645861854958e-01 7.04692046391145e-02 2.55928809695428e-01 - 7.67740309924711e-02 2.66220088966340e-01 + 7.67740309924709e-02 2.66220088966340e-01 8.34162127168367e-02 2.76507393790272e-01 - 9.04290195190654e-02 2.86789711779561e-01 + 9.04290195190656e-02 2.86789711779561e-01 9.77906533229447e-02 2.97034361595414e-01 1.05536187198748e-01 3.07245770330167e-01 1.13658760041779e-01 3.17397798197942e-01 1.22161483318940e-01 3.27472514118938e-01 - 1.31067498602735e-01 3.37467155091885e-01 + 1.31067498602735e-01 3.37467155091884e-01 1.40354649921884e-01 3.47346400530541e-01 1.50055110786138e-01 3.57117293892256e-01 1.60148962661562e-01 3.66736829146265e-01 @@ -149,7 +149,7 @@ 1.81574957422924e-01 3.85495420277773e-01 1.92907571409635e-01 3.94583247665971e-01 2.04657634577812e-01 4.03452252859203e-01 - 2.16817353069425e-01 4.12073654675103e-01 + 2.16817353069424e-01 4.12073654675103e-01 2.29396483963478e-01 4.20441260405522e-01 2.42377800694080e-01 4.28515729124923e-01 2.55773624268338e-01 4.36297014051329e-01 @@ -157,7 +157,7 @@ 2.83765797226135e-01 4.50825718973627e-01 2.98347982887804e-01 4.57529313046837e-01 3.13318978785268e-01 4.63848274999177e-01 - 3.28658461892810e-01 4.69727033948470e-01 + 3.28658461892810e-01 4.69727033948469e-01 3.44364941645546e-01 4.75166089488011e-01 3.60419773725681e-01 4.80124895665173e-01 3.76811233766957e-01 4.84580156948735e-01 @@ -178,7 +178,7 @@ 6.48926781663159e-01 4.77299436027394e-01 6.67570206424973e-01 4.71090906382616e-01 6.86088429590952e-01 4.64085564448580e-01 - 7.04445389043917e-01 4.56285153530383e-01 + 7.04445389043917e-01 4.56285153530384e-01 7.22592093722966e-01 4.47721154132331e-01 7.40501800453524e-01 4.38357128523673e-01 7.58125457122835e-01 4.28212344239085e-01 @@ -194,8 +194,8 @@ 9.09954680076662e-01 2.86240968660934e-01 9.21851471402547e-01 2.68396507929684e-01 9.33012836658427e-01 2.50001405518451e-01 - 9.43389278969050e-01 2.31088842332577e-01 - 9.52973153850560e-01 2.11684808241657e-01 + 9.43389278969050e-01 2.31088842332578e-01 + 9.52973153850559e-01 2.11684808241657e-01 9.61743130827061e-01 1.91832340326070e-01 9.69640690675464e-01 1.71577158818629e-01 9.76664215898664e-01 1.50951670528481e-01 @@ -205,4 +205,4 @@ 9.95693518775914e-01 6.56397719044068e-02 9.98120489340015e-01 4.38394581414280e-02 9.99443037908705e-01 2.19496513968833e-02 - 1.00000000000000e+00 -5.26302389882222e-16 + 1.00000000000000e+00 -5.26828685157063e-16 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF01_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF01_Coords.txt new file mode 100644 index 00000000..2957c417 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF01_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.499996 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 1.40005998995553e-08 + 9.99429427343441e-01 -2.22597267030057e-02 + 9.98061572217025e-01 -4.44577848805880e-02 + 9.95571383549524e-01 -6.65613532214902e-02 + 9.92082809827900e-01 -8.85193855241323e-02 + 9.87681777703418e-01 -1.10274914777896e-01 + 9.82325363018063e-01 -1.31784096290399e-01 + 9.76006023234194e-01 -1.53006417256835e-01 + 9.68780907279161e-01 -1.73886649853821e-01 + 9.60667684160886e-01 -1.94379246532870e-01 + 9.51667600623758e-01 -2.14449599639644e-01 + 9.41819346367688e-01 -2.34058280560842e-01 + 9.31166468996032e-01 -2.53152837999437e-01 + 9.19721069411155e-01 -2.71705651589515e-01 + 9.07514754074885e-01 -2.89690709437295e-01 + 8.94600146303824e-01 -3.07057071448252e-01 + 8.80998997819370e-01 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7.04431826856421e-01 4.56281232320674e-01 + 7.22578683995759e-01 4.47717549871310e-01 + 7.40488571062978e-01 4.38353834215016e-01 + 7.58112436634799e-01 4.28209350234295e-01 + 7.75408233050915e-01 4.17300188381259e-01 + 7.92349858684666e-01 4.05611562914235e-01 + 8.08882327912338e-01 3.93171409150622e-01 + 8.24962738826757e-01 3.79988508650156e-01 + 8.40565414246071e-01 3.66061008171375e-01 + 8.55641607139505e-01 3.51431756036478e-01 + 8.70152165931217e-01 3.36116704625257e-01 + 8.84074751506678e-01 3.20124680972120e-01 + 8.97351411193486e-01 3.03489770031700e-01 + 9.09945391979414e-01 2.86240427891614e-01 + 9.21842722709060e-01 2.68396129636527e-01 + 9.33004662474069e-01 2.50001181727226e-01 + 9.43381712415969e-01 2.31088757323814e-01 + 9.52966225012817e-01 2.11684822173323e-01 + 9.61736865408470e-01 1.91832354266127e-01 + 9.69635124673369e-01 1.71577172767025e-01 + 9.76659380194314e-01 1.50951684485025e-01 + 9.82810991312600e-01 1.29995634996227e-01 + 9.88025141194105e-01 1.08765313129958e-01 + 9.92302353521589e-01 8.72999477295311e-02 + 9.95691879580707e-01 6.56397858905899e-02 + 9.98119706513454e-01 4.38394721340010e-02 + 9.99443037892454e-01 2.19495558180643e-02 + 1.00000000000000e+00 1.40005998955560e-08 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF02_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF02_Coords.txt new file mode 100644 index 00000000..389bc00f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF02_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.489918 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 3.11697462695050e-05 + 9.98792778568247e-01 -2.21849423041560e-02 + 9.94709408491515e-01 -4.37908234181668e-02 + 9.89719063295889e-01 -6.53727690708149e-02 + 9.83991827465383e-01 -8.73255711462479e-02 + 9.77577544450589e-01 -1.09195210069932e-01 + 9.70392217269295e-01 -1.30834838408396e-01 + 9.62401646816373e-01 -1.52173369026241e-01 + 9.53616308899169e-01 -1.73115133554863e-01 + 9.44078883004556e-01 -1.93680593662128e-01 + 9.33733219711924e-01 -2.13750078995666e-01 + 9.22617429104402e-01 -2.33300650528889e-01 + 9.10762170100885e-01 -2.52279090934922e-01 + 8.98156414009905e-01 -2.70625520679034e-01 + 8.84846129275043e-01 -2.88347042474457e-01 + 8.70874303459625e-01 -3.05384058067013e-01 + 8.56260886787625e-01 -3.21707707821992e-01 + 8.41038766618914e-01 -3.37311442868568e-01 + 8.25275040762271e-01 -3.52170492383091e-01 + 8.09008886199076e-01 -3.66277538730936e-01 + 7.92262956278720e-01 -3.79607791787505e-01 + 7.75095050375002e-01 -3.92112513883925e-01 + 7.57573075377607e-01 -4.03828412252961e-01 + 7.39693488744078e-01 -4.14694049879667e-01 + 7.21536831733535e-01 -4.24776824918018e-01 + 7.03121906177338e-01 -4.33979348845875e-01 + 6.84493387002760e-01 -4.42380666276484e-01 + 6.65709831803348e-01 -4.49974222078074e-01 + 6.46803647185148e-01 -4.56746323538791e-01 + 6.27805282572633e-01 -4.62702508266310e-01 + 6.08769029639549e-01 -4.67880733533020e-01 + 5.89723320072293e-01 -4.72223025923308e-01 + 5.70703750587007e-01 -4.75837794352136e-01 + 5.51753388247683e-01 -4.78661069500781e-01 + 5.32894094697214e-01 -4.80798687608076e-01 + 5.14169356823052e-01 -4.82158133294204e-01 + 4.95605216535442e-01 -4.82726789956120e-01 + 4.77219158997371e-01 -4.82728572489828e-01 + 4.59055571265520e-01 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1.08638869933479e-01 + 9.86536727763238e-01 8.72134512733374e-02 + 9.91867220169214e-01 6.55920450585678e-02 + 9.96259556749258e-01 4.38267465817332e-02 + 9.99379643516300e-01 2.17316622733827e-02 + 1.00000000000000e+00 3.11697462695010e-05 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF03_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF03_Coords.txt new file mode 100644 index 00000000..368cd8bd --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF03_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.464392 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 9.44054819368640e-05 + 9.96923783298513e-01 -2.16438857098048e-02 + 9.86750962146060e-01 -4.14648205105703e-02 + 9.75991940468785e-01 -6.15137163516908e-02 + 9.65054205115156e-01 -8.29184804485191e-02 + 9.53940472019856e-01 -1.04509064076945e-01 + 9.42481677594047e-01 -1.25943826183654e-01 + 9.30584488398964e-01 -1.47091057342449e-01 + 9.18152274541527e-01 -1.67773905302460e-01 + 9.05285329921781e-01 -1.88133263858891e-01 + 8.91795320505773e-01 -2.07888065972100e-01 + 8.77718618321606e-01 -2.27044077070090e-01 + 8.63055486968971e-01 -2.45542766434707e-01 + 8.47740515603274e-01 -2.63260380854480e-01 + 8.31851888031741e-01 -2.80261881632504e-01 + 8.15409145254910e-01 -2.96468979128058e-01 + 7.98426927866672e-01 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4.90582070152980e-02 1.94736994989385e-01 + 5.35340018637743e-02 2.03115244822406e-01 + 5.82837915297898e-02 2.11547642695091e-01 + 6.33351801667874e-02 2.20033140707549e-01 + 6.86401251468436e-02 2.28569934803754e-01 + 7.42272548120636e-02 2.37163318012591e-01 + 8.01196560476374e-02 2.45788663448382e-01 + 8.63307082083169e-02 2.54429538603770e-01 + 9.28250826404981e-02 2.63119655632924e-01 + 9.96151523489584e-02 2.71823596011513e-01 + 1.06771709719796e-01 2.80522656428195e-01 + 1.14289871889533e-01 2.89185047380688e-01 + 1.22165975516914e-01 2.97828593551331e-01 + 1.30403868764262e-01 3.06427230443892e-01 + 1.38990200919880e-01 3.14995426949833e-01 + 1.47969751776653e-01 3.23485724226965e-01 + 1.57361528045221e-01 3.31862218154845e-01 + 1.67144419888203e-01 3.40154287933799e-01 + 1.77307898151855e-01 3.48338254267513e-01 + 1.87889764546787e-01 3.56387986084499e-01 + 1.98897359073543e-01 3.64245898865723e-01 + 2.10347619668173e-01 3.71910444037256e-01 + 2.22236708320681e-01 3.79330943328417e-01 + 2.34588282889992e-01 3.86479706550197e-01 + 2.47343811156454e-01 3.93391935249739e-01 + 2.60582145900602e-01 3.99925054005489e-01 + 2.74225101658487e-01 4.06178193307188e-01 + 2.88315125174728e-01 4.12032656000221e-01 + 3.02825054140620e-01 4.17529143471988e-01 + 3.17763150799911e-01 4.22553357869358e-01 + 3.33104610358311e-01 4.27197423676452e-01 + 3.48838348510863e-01 4.31315435147126e-01 + 3.64970051727677e-01 4.34971337039456e-01 + 3.81483853494839e-01 4.37904127638067e-01 + 3.98361605944391e-01 4.40358878565305e-01 + 4.15570857179751e-01 4.42114230352512e-01 + 4.33088650986587e-01 4.43373980371240e-01 + 4.50902925376936e-01 4.43820367304233e-01 + 4.68972912267664e-01 4.43660461110881e-01 + 4.87287044378984e-01 4.42717023231123e-01 + 5.05803713812534e-01 4.41119875712370e-01 + 5.24498972573167e-01 4.38689845156700e-01 + 5.43343697751625e-01 4.35466871955895e-01 + 5.62302254742289e-01 4.31642876475118e-01 + 5.81330045863197e-01 4.26804120992610e-01 + 6.00417829020494e-01 4.21312934747846e-01 + 6.19511743354015e-01 4.15008517656744e-01 + 6.38582778349824e-01 4.07867738242271e-01 + 6.57589012927152e-01 3.99893003231071e-01 + 6.76641999006394e-01 3.91149198139106e-01 + 6.95677552572029e-01 3.81537221304609e-01 + 7.14531035702312e-01 3.71137756894499e-01 + 7.33137095171979e-01 3.59873484886580e-01 + 7.51507481541476e-01 3.47864259882383e-01 + 7.69578488761687e-01 3.35088699792006e-01 + 7.87327996086565e-01 3.21582528180890e-01 + 8.04736157831846e-01 3.07372723953618e-01 + 8.21702404223314e-01 2.92359267564169e-01 + 8.38262336688405e-01 2.76726564554491e-01 + 8.54310027807165e-01 2.60304976363149e-01 + 8.69888471938163e-01 2.43294208306092e-01 + 8.84933040739667e-01 2.25678262925529e-01 + 8.99412990874286e-01 2.07349933198512e-01 + 9.13274206761712e-01 1.88030204854370e-01 + 9.26534822813331e-01 1.68305625002896e-01 + 9.39153653193120e-01 1.48200110006822e-01 + 9.51047733036157e-01 1.27734922212462e-01 + 9.62277182402837e-01 1.06992408688949e-01 + 9.72775366334289e-01 8.59988926685764e-02 + 9.82570741487315e-01 6.47976208557021e-02 + 9.91447684039704e-01 4.34144664477603e-02 + 9.98692576247939e-01 2.12471865113030e-02 + 1.00000000000000e+00 9.44054819368601e-05 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF04_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF04_Coords.txt new file mode 100644 index 00000000..8c8f40c8 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF04_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.429199 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 1.50639922379954e-04 + 9.93825116368402e-01 -2.01670270052505e-02 + 9.76971987326442e-01 -3.69812411596295e-02 + 9.59638397286645e-01 -5.44835138995675e-02 + 9.42670484767148e-01 -7.40752376060517e-02 + 9.26075454307312e-01 -9.41658668399325e-02 + 9.09612465731644e-01 -1.14270937651071e-01 + 8.93131208613358e-01 -1.34205585833426e-01 + 8.76422509204268e-01 -1.53719854855478e-01 + 8.59647113144997e-01 -1.73031717041737e-01 + 8.42478302881929e-01 -1.91739038477861e-01 + 8.24949233510082e-01 -2.09862208046166e-01 + 8.07025539322051e-01 -2.27328741382489e-01 + 7.88582181958697e-01 -2.43960372721002e-01 + 7.69728270043092e-01 -2.59852875597655e-01 + 7.50455066159919e-01 -2.74908585527527e-01 + 7.30768856519934e-01 -2.89076976991922e-01 + 7.10734026134789e-01 -3.02376826658361e-01 + 6.90422680344192e-01 -3.14812442583619e-01 + 6.69903396291527e-01 -3.26415097769023e-01 + 6.49169995960853e-01 -3.37088841903011e-01 + 6.28563073441194e-01 -3.46755218272321e-01 + 6.08509490129302e-01 -3.55617618354979e-01 + 5.88400336356101e-01 -3.63369617620486e-01 + 5.68374089867870e-01 -3.70391271833192e-01 + 5.48387946757785e-01 -3.76295993225084e-01 + 5.28528608275514e-01 -3.81353165320938e-01 + 5.08846887080833e-01 -3.85637754433315e-01 + 4.89365481111481e-01 -3.89079456754792e-01 + 4.70108182934207e-01 -3.91575047384096e-01 + 4.51124851331427e-01 -3.93489986934023e-01 + 4.32436462955731e-01 -3.94413108497312e-01 + 4.14068667962057e-01 -3.94707698622192e-01 + 3.96047116672700e-01 -3.94318693947774e-01 + 3.78390499420695e-01 -3.93354324010347e-01 + 3.61137089527507e-01 -3.91548081278938e-01 + 3.44294262447928e-01 -3.89144050245470e-01 + 3.27852553763786e-01 -3.86313239577107e-01 + 3.11856910640169e-01 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-2.28508364459162e-01 + 7.33340312050618e-02 -2.20433078553628e-01 + 6.80324951643100e-02 -2.12423844224058e-01 + 6.30417193529091e-02 -2.04519589897441e-01 + 5.83096301105653e-02 -1.96738239042999e-01 + 5.38016390606915e-02 -1.89111749869821e-01 + 4.96026898349437e-02 -1.81573205636937e-01 + 4.56327250695242e-02 -1.74166237430730e-01 + 4.18728914299956e-02 -1.66908046187620e-01 + 3.83174841791309e-02 -1.59777426145505e-01 + 3.50253608418105e-02 -1.52744961961351e-01 + 3.19445600042997e-02 -1.45831978051611e-01 + 2.90724119757712e-02 -1.39034908418031e-01 + 2.64232301587887e-02 -1.32351735741685e-01 + 2.39626958976056e-02 -1.25784513945137e-01 + 2.16748388246736e-02 -1.19343967050697e-01 + 1.95686259725624e-02 -1.13036379516507e-01 + 1.76053997713580e-02 -1.06850421467632e-01 + 1.57497466369458e-02 -1.00803849074163e-01 + 1.40158065499312e-02 -9.48901710130890e-02 + 1.24332126478387e-02 -8.90919199421619e-02 + 1.09877052526025e-02 -8.34147315179866e-02 + 9.63942188616484e-03 -7.78597941994217e-02 + 8.35447583749980e-03 -7.24262572688269e-02 + 7.17553290706620e-03 -6.71089909824489e-02 + 6.12877579024111e-03 -6.19011409871098e-02 + 5.18027470035278e-03 -5.67991574211783e-02 + 4.32401943590811e-03 -5.18083870672683e-02 + 3.55844111108688e-03 -4.69311010931079e-02 + 2.86522285717555e-03 -4.21601809598737e-02 + 2.27242618501838e-03 -3.74930736631853e-02 + 1.78041086322702e-03 -3.29313900634512e-02 + 1.34314904948014e-03 -2.84760249354099e-02 + 8.96198113115433e-04 -2.41260415803860e-02 + 5.10589108473089e-04 -1.98784774376619e-02 + 3.13796101731496e-04 -1.57260192705604e-02 + 1.76931660052504e-04 -1.16676808380940e-02 + 7.31448679043374e-05 -7.70233033114123e-03 + 1.97228468786147e-05 -3.83031315690182e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 3.23306824296959e-05 3.72663760311781e-03 + 1.29842674153680e-04 7.58559479913837e-03 + 3.10081443685023e-04 1.15413021098891e-02 + 5.34175271530997e-04 1.55883377180133e-02 + 7.77152319438240e-04 1.97335475789882e-02 + 1.09802529851270e-03 2.39796840741796e-02 + 1.48368545053408e-03 2.83248657758363e-02 + 1.92446278035036e-03 3.27656263613764e-02 + 2.47888270136373e-03 3.73047268274936e-02 + 3.13315292994846e-03 4.19485432520312e-02 + 3.83234808731443e-03 4.66997247150635e-02 + 4.58839870416647e-03 5.15566824674854e-02 + 5.45473965839827e-03 5.65208773220767e-02 + 6.44974794170204e-03 6.15868944177101e-02 + 7.54398102125260e-03 6.67547293364322e-02 + 8.71923053151525e-03 7.20365835154547e-02 + 9.97272064222359e-03 7.74366824831880e-02 + 1.13178129442358e-02 8.29463643557327e-02 + 1.28076469063735e-02 8.85616422008356e-02 + 1.44563388047050e-02 9.42910710278974e-02 + 1.61965269525356e-02 1.00140630615420e-01 + 1.80168045911478e-02 1.06124768404076e-01 + 1.99614335193230e-02 1.12234652048844e-01 + 2.20726908655543e-02 1.18459733560101e-01 + 2.43585800269142e-02 1.24810864894382e-01 + 2.67979124316423e-02 1.31294474255796e-01 + 2.94278739166264e-02 1.37882348361615e-01 + 3.22919926639024e-02 1.44572014378606e-01 + 3.53649139865357e-02 1.51368765404054e-01 + 3.86591409452920e-02 1.58265541671239e-01 + 4.21974635494740e-02 1.65261181996845e-01 + 4.59247472271020e-02 1.72377550006574e-01 + 4.98656244423393e-02 1.79620086838866e-01 + 5.40592509385260e-02 1.86965537305978e-01 + 5.85243769111221e-02 1.94398732948545e-01 + 6.31979115971898e-02 2.01980098633252e-01 + 6.81125413121970e-02 2.09674320058645e-01 + 7.33547192592396e-02 2.17442861738183e-01 + 7.89304832578431e-02 2.25262731903794e-01 + 8.48229713319361e-02 2.33161165892639e-01 + 9.10449808647500e-02 2.41121083235135e-01 + 9.75742264002897e-02 2.49175858078168e-01 + 1.04476346466662e-01 2.57257765775008e-01 + 1.11785494672608e-01 2.65325415827440e-01 + 1.19467672549980e-01 2.73432039012652e-01 + 1.27518633452080e-01 2.81564539077503e-01 + 1.35987281733138e-01 2.89676569175103e-01 + 1.44894924712119e-01 2.97708684938950e-01 + 1.54263555784105e-01 3.05649488788744e-01 + 1.64101715818601e-01 3.13449669423272e-01 + 1.74440928411978e-01 3.21056432370502e-01 + 1.85207863158729e-01 3.28567008077067e-01 + 1.96519173107261e-01 3.35740810051744e-01 + 2.08272075662548e-01 3.42770022795852e-01 + 2.20536068534141e-01 3.49471328328863e-01 + 2.33279958722219e-01 3.55905702858263e-01 + 2.46529222394472e-01 3.61940357346035e-01 + 2.60252225740409e-01 3.67670459668533e-01 + 2.74451459858811e-01 3.72970852102391e-01 + 2.89138855597453e-01 3.77839525061369e-01 + 3.04313084112333e-01 3.82052989411498e-01 + 3.19954938463797e-01 3.85770965089497e-01 + 3.36034754255422e-01 3.88873528917721e-01 + 3.52535721344842e-01 3.91480301466176e-01 + 3.69451127691435e-01 3.93336279360581e-01 + 3.86747314472571e-01 3.94603579924491e-01 + 4.04418022023886e-01 3.95116376365675e-01 + 4.22424791004886e-01 3.95019905492055e-01 + 4.40752901649959e-01 3.94058304397881e-01 + 4.59373948550652e-01 3.92327943670238e-01 + 4.78265724943047e-01 3.90092528994945e-01 + 4.97378872095490e-01 3.86744562805955e-01 + 5.16720075862136e-01 3.82843406891621e-01 + 5.36238572801128e-01 3.78123143252654e-01 + 5.55906913054693e-01 3.72572146337360e-01 + 5.75691711285939e-01 3.66184446680063e-01 + 5.95989506053998e-01 3.59050371343162e-01 + 6.16690238612756e-01 3.51030246602093e-01 + 6.37388476336622e-01 3.42232192366278e-01 + 6.58002490204530e-01 3.32536554998071e-01 + 6.78573545238263e-01 3.22127255227523e-01 + 6.99027449451809e-01 3.10948293862190e-01 + 7.19355919018514e-01 2.99046363871560e-01 + 7.39541366389923e-01 2.86457949055682e-01 + 7.59452964048431e-01 2.73017120543956e-01 + 7.79180881289212e-01 2.58984351678540e-01 + 7.98551940870688e-01 2.44099307892628e-01 + 8.17669709634573e-01 2.28633839510729e-01 + 8.36459324162845e-01 2.12547754047013e-01 + 8.54873127475182e-01 1.95705210243350e-01 + 8.72833930178459e-01 1.77766690176499e-01 + 8.90414437832225e-01 1.59422281728604e-01 + 9.07543565525050e-01 1.40675829265513e-01 + 9.24078419056890e-01 1.21504746192956e-01 + 9.40161494789802e-01 1.02051949436287e-01 + 9.55671164053353e-01 8.23129122740457e-02 + 9.70600424067586e-01 6.23378928523766e-02 + 9.84603867784436e-01 4.20837899026943e-02 + 9.96687665857578e-01 2.07285752768550e-02 + 1.00000000000000e+00 1.50639922379950e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF05_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF05_Coords.txt new file mode 100644 index 00000000..1cf36c83 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF05_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.390122 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 1.81668005709887e-04 + 9.89839305056369e-01 -1.77184371943406e-02 + 9.67669339123546e-01 -3.06948948775324e-02 + 9.45029140738328e-01 -4.49130889238079e-02 + 9.23087530488359e-01 -6.14315900824870e-02 + 9.01887757603543e-01 -7.87543056701497e-02 + 8.81172905135403e-01 -9.63551365927508e-02 + 8.60771720344449e-01 -1.14015052624867e-01 + 8.40414525195301e-01 -1.31435582891476e-01 + 8.20293195088020e-01 -1.48837630563814e-01 + 8.00010762556257e-01 -1.65775916796712e-01 + 7.79595375442742e-01 -1.82263687689669e-01 + 7.58987845782886e-01 -1.98206422874963e-01 + 7.38027941878539e-01 -2.13395760860541e-01 + 7.16833953238522e-01 -2.27917465130822e-01 + 6.95374613969084e-01 -2.41658888140446e-01 + 6.73646884772149e-01 -2.54554595075268e-01 + 6.51718617874821e-01 -2.66614958541719e-01 + 6.29655663927714e-01 -2.77841210845614e-01 + 6.07531359156390e-01 -2.88265150357909e-01 + 5.85328095390029e-01 -2.97774729393737e-01 + 5.63542105624344e-01 -3.06287094687590e-01 + 5.42770334931897e-01 -3.14025179968140e-01 + 5.22094612382781e-01 -3.20644740726036e-01 + 5.01650729116227e-01 -3.26567441178945e-01 + 4.81384772528712e-01 -3.31363993863077e-01 + 4.61383492166413e-01 -3.35320979201823e-01 + 4.41689840160337e-01 -3.38529316294309e-01 + 4.22323271382687e-01 -3.40913006721076e-01 + 4.03304573677797e-01 -3.42348856822591e-01 + 3.84676771933928e-01 -3.43264104397781e-01 + 3.66457374341614e-01 -3.43186694158794e-01 + 3.48666802185297e-01 -3.42520002320538e-01 + 3.31322895319195e-01 -3.41222232657113e-01 + 3.14441847163063e-01 -3.39390980462570e-01 + 2.98055303743063e-01 -3.36740879405174e-01 + 2.82164639931318e-01 -3.33568103087579e-01 + 2.66754333859033e-01 -3.30012524744029e-01 + 2.51862721994187e-01 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-5.21010683635556e-02 + 4.61668756263021e-03 -4.82538055469151e-02 + 3.94908820272010e-03 -4.45218740465887e-02 + 3.36454091770521e-03 -4.08947994530565e-02 + 2.84331452650350e-03 -3.73696441339502e-02 + 2.37225751851325e-03 -3.39494194552734e-02 + 1.94332294947207e-03 -3.06339975179006e-02 + 1.55954669828877e-03 -2.74165026047054e-02 + 1.24562186231914e-03 -2.42920931203457e-02 + 9.89133064825562e-04 -2.12601146741595e-02 + 7.52124710834712e-04 -1.83214518341754e-02 + 4.84550621080101e-04 -1.54763017477014e-02 + 2.42145727570053e-04 -1.27189350164608e-02 + 1.43601595034255e-04 -1.00384612097229e-02 + 7.61873786880223e-05 -7.43483205109773e-03 + 2.84602487828866e-05 -4.90719320558744e-03 + 7.70462178850949e-06 -2.45437672700742e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.29154496308512e-05 2.30454879669094e-03 + 9.21277039078369e-05 4.73999917422172e-03 + 2.22158261301634e-04 7.25795687632589e-03 + 3.86336189929779e-04 9.85079113653697e-03 + 5.37981292386847e-04 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1.89642714914147e-02 1.02161688611462e-01 + 2.09447333410899e-02 1.07570952065851e-01 + 2.31022417167603e-02 1.13113768999875e-01 + 2.54554679096700e-02 1.18788809943084e-01 + 2.79540424979398e-02 1.24632603973116e-01 + 3.06202336972029e-02 1.30649462837102e-01 + 3.35002647999872e-02 1.36818455258026e-01 + 3.66150920439140e-02 1.43126272611735e-01 + 3.98934867965818e-02 1.49646886031458e-01 + 4.33790848832209e-02 1.56347098816828e-01 + 4.71595194395097e-02 1.63176570648299e-01 + 5.12488498413124e-02 1.70119587006001e-01 + 5.56250426590652e-02 1.77207210896758e-01 + 6.03078585705348e-02 1.84428398149115e-01 + 6.52741078779166e-02 1.91825628824162e-01 + 7.05960008616806e-02 1.99321258721810e-01 + 7.63152181327329e-02 2.06871706727953e-01 + 8.23962358413367e-02 2.14540127410422e-01 + 8.88406036666841e-02 2.22320251007191e-01 + 9.56992111484199e-02 2.30153834408643e-01 + 1.03000430140358e-01 2.37983823891040e-01 + 1.10769080690412e-01 2.45789533863714e-01 + 1.19021710029169e-01 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4.48458197315896e-01 3.36689857074510e-01 + 4.68069080793735e-01 3.33150251906539e-01 + 4.87971013509052e-01 3.28831395554929e-01 + 5.08139676667431e-01 3.23724149994242e-01 + 5.29199337639026e-01 3.17926561401568e-01 + 5.51009573812084e-01 3.11289602543246e-01 + 5.72971568866073e-01 3.03929868302021e-01 + 5.94997674795123e-01 2.95715291323927e-01 + 6.17146860415960e-01 2.86853571430211e-01 + 6.39342374165498e-01 2.77273429753645e-01 + 6.61586002485230e-01 2.67026206816235e-01 + 6.83862351866883e-01 2.56151886709350e-01 + 7.06028612592097e-01 2.44463249705942e-01 + 7.28205984217708e-01 2.32243197464589e-01 + 7.50186313263602e-01 2.19204659507964e-01 + 7.72106536177158e-01 2.05635795266837e-01 + 7.93889294437484e-01 1.91487841374586e-01 + 8.15477683809172e-01 1.76660212602995e-01 + 8.36783185673207e-01 1.60911879801007e-01 + 8.57908949389615e-01 1.44766830357707e-01 + 8.78766841681439e-01 1.28201738912787e-01 + 8.99182352646326e-01 1.11134260753372e-01 + 9.19339872446482e-01 9.37865800802753e-02 + 9.39084931241369e-01 7.61115156931585e-02 + 9.58378822750075e-01 5.81686063506184e-02 + 9.76799750962106e-01 3.98188665560602e-02 + 9.93366181728805e-01 2.03406423565705e-02 + 1.00000000000000e+00 1.81668005709885e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF06_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF06_Coords.txt new file mode 100644 index 00000000..ab19c838 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF06_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.352942 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 1.91618246389726e-04 + 9.85713728297364e-01 -1.48145073454067e-02 + 9.60296599608518e-01 -2.39280828741916e-02 + 9.34667548395100e-01 -3.47369900568018e-02 + 9.09826473042007e-01 -4.77134739187086e-02 + 8.85816893608743e-01 -6.17785901066344e-02 + 8.62429370848723e-01 -7.64247120957726e-02 + 8.39522344092125e-01 -9.14077524240148e-02 + 8.16847406253680e-01 -1.06394463238442e-01 + 7.94581185412904e-01 -1.21567772853087e-01 + 7.72363998526917e-01 -1.36482245585183e-01 + 7.50217564651659e-01 -1.51132558724339e-01 + 7.28076023083174e-01 -1.65399569075069e-01 + 7.05785739491298e-01 -1.79060380032277e-01 + 6.83442761543389e-01 -1.92171344884600e-01 + 6.61006394925856e-01 -2.04609732855716e-01 + 6.38466096824721e-01 -2.16297357943611e-01 + 6.15876941845506e-01 -2.27230602266142e-01 + 5.93288984977918e-01 -2.37402498007493e-01 + 5.70765409009589e-01 -2.46838668993632e-01 + 5.48286421870134e-01 -2.55424144944172e-01 + 5.26269937255425e-01 -2.63080327516458e-01 + 5.05230893642848e-01 -2.70017786709455e-01 + 4.84381081773310e-01 -2.75905633470131e-01 + 4.63844631838532e-01 -2.81143346814918e-01 + 4.43567047481127e-01 -2.85322762886107e-01 + 4.23628476217602e-01 -2.88704816117099e-01 + 4.04065787454561e-01 -2.91379499387231e-01 + 3.84896956627907e-01 -2.93279659130418e-01 + 3.66141031047616e-01 -2.94289117105526e-01 + 3.47835383469268e-01 -2.94820173885516e-01 + 3.29995476666150e-01 -2.94428000841823e-01 + 3.12638443975118e-01 -2.93490557506629e-01 + 2.95777618769517e-01 -2.91981345539914e-01 + 2.79427374749891e-01 -2.89980004165011e-01 + 2.63614021350148e-01 -2.87237496984430e-01 + 2.48336307207790e-01 -2.84033070995830e-01 + 2.33577341419421e-01 -2.80476925004388e-01 + 2.19369226120868e-01 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8.41638363973287e-02 + 9.25571740404426e-01 6.88571585006190e-02 + 9.47766649722456e-01 5.32678502667369e-02 + 9.69305372052072e-01 3.71731888356646e-02 + 9.89520674918417e-01 2.01386433906473e-02 + 1.00000000000000e+00 1.91618246389725e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF07_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF07_Coords.txt new file mode 100644 index 00000000..c5d0f4f7 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF07_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.323441 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 1.92868919692344e-04 + 9.82407475246458e-01 -1.23088621078325e-02 + 9.55513540141175e-01 -1.84426823965055e-02 + 9.28969001281695e-01 -2.65113990168809e-02 + 9.03155234426800e-01 -3.65722603048777e-02 + 8.78057554433568e-01 -4.79584156464652e-02 + 8.53544566995996e-01 -6.01827214828987e-02 + 8.29534703869550e-01 -7.29770070036873e-02 + 8.05856309159957e-01 -8.59768766108782e-02 + 7.82639514189691e-01 -9.93317942847610e-02 + 7.59634088512754e-01 -1.12595603368092e-01 + 7.36855530895818e-01 -1.25747146875780e-01 + 7.14245874307582e-01 -1.38647334434625e-01 + 6.91688200575899e-01 -1.51062355357102e-01 + 6.69237531285970e-01 -1.63025938039175e-01 + 6.46855550444046e-01 -1.74408997915636e-01 + 6.24527581747874e-01 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7.60908177448896e-02 + 9.16514012348515e-01 6.27440350716847e-02 + 9.40175790838216e-01 4.91222930110910e-02 + 9.63518168850016e-01 3.49576047477060e-02 + 9.86307215423474e-01 2.00813324173578e-02 + 1.00000000000000e+00 1.92868919692345e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF08_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF08_Coords.txt new file mode 100644 index 00000000..31c8dad7 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF08_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.303523 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 1.67793866277612e-04 + 9.80105439787502e-01 -1.01813197115048e-02 + 9.52881851296265e-01 -1.45034730859470e-02 + 9.26360534807159e-01 -2.11063901993153e-02 + 9.00451901565177e-01 -2.92494156531073e-02 + 8.75109122021321e-01 -3.89270282693225e-02 + 8.50271015533919e-01 -4.96697763073901e-02 + 8.25908437538160e-01 -6.11701168487462e-02 + 8.01920278660714e-01 -7.30285092572216e-02 + 7.78394863715461e-01 -8.53480042114618e-02 + 7.55179956966922e-01 -9.76991513951347e-02 + 7.32286562360959e-01 -1.10042089420031e-01 + 7.09666233443598e-01 -1.22219616613677e-01 + 6.87235986475062e-01 -1.33992991143745e-01 + 6.65016108346109e-01 -1.45372991140821e-01 + 6.42972746653797e-01 -1.56228160833990e-01 + 6.21088611075758e-01 -1.66468211136151e-01 + 5.99378068084506e-01 -1.76072647272961e-01 + 5.77855727260433e-01 -1.85024979936861e-01 + 5.56549066498367e-01 -1.93343490870287e-01 + 5.35449445977407e-01 -2.00920241460509e-01 + 5.14406667343370e-01 -2.07691971229675e-01 + 4.93350439358222e-01 -2.13837048657096e-01 + 4.72516939000228e-01 -2.19080001913305e-01 + 4.52021703891012e-01 -2.23749808790863e-01 + 4.31812756436607e-01 -2.27515661219660e-01 + 4.11964839916347e-01 -2.30576182816174e-01 + 3.92511996492597e-01 -2.33006352470674e-01 + 3.73471819369622e-01 -2.34764059833324e-01 + 3.54862711771932e-01 -2.35768601126550e-01 + 3.36719297091692e-01 -2.36342167216018e-01 + 3.19056286691240e-01 -2.36159538177877e-01 + 3.01889558989936e-01 -2.35502949996681e-01 + 2.85230945717454e-01 -2.34365862294414e-01 + 2.69093996076186e-01 -2.32795433716121e-01 + 2.53502477339550e-01 -2.30649802962872e-01 + 2.38454688011670e-01 -2.28108601892027e-01 + 2.23934372473248e-01 -2.25241257029010e-01 + 2.09970340755282e-01 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-2.94783265364546e-02 + 1.90570576407697e-03 -2.70802885451037e-02 + 1.61757192233294e-03 -2.47829164400676e-02 + 1.37116041945252e-03 -2.25814653443132e-02 + 1.15959047603326e-03 -2.04716690940801e-02 + 9.68523619176466e-04 -1.84508094108964e-02 + 7.86183232545318e-04 -1.65158372378438e-02 + 6.29441712929409e-04 -1.46625654363367e-02 + 5.16781109221284e-04 -1.28867310723137e-02 + 4.28847917262679e-04 -1.11857285815879e-02 + 3.39307093085431e-04 -9.55817943290215e-03 + 2.13607534099717e-04 -8.00243423393045e-03 + 8.79892297910428e-05 -6.51462953687812e-03 + 5.62413408267618e-05 -5.08904035500971e-03 + 3.30209949737755e-05 -3.72420136673376e-03 + 1.67772553804997e-05 -2.41816232733398e-03 + 7.08273306194318e-06 -1.16920300661154e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.15390322376342e-05 1.21594717858823e-03 + 7.63154960772153e-05 2.46686226317518e-03 + 1.66646423722692e-04 3.76789306495500e-03 + 2.80944227366391e-04 5.12681399631580e-03 + 3.64997876570869e-04 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1.71193865571847e-01 + 9.52882446049826e-02 1.76583361938397e-01 + 1.03407890211844e-01 1.81939396877310e-01 + 1.12095568124396e-01 1.87110187310814e-01 + 1.21260703453365e-01 1.92208177595947e-01 + 1.30977793285880e-01 1.97595036226115e-01 + 1.41223082023593e-01 2.02826723508190e-01 + 1.52030163683463e-01 2.07687481305033e-01 + 1.63370961888235e-01 2.12270496676546e-01 + 1.75260124055786e-01 2.16559677991882e-01 + 1.87710976474859e-01 2.20516454052570e-01 + 2.00735532928886e-01 2.24079082778616e-01 + 2.14318521810095e-01 2.27258775216194e-01 + 2.28442102766429e-01 2.30074271835432e-01 + 2.43099898227201e-01 2.32507848690467e-01 + 2.58291626392007e-01 2.34519106222378e-01 + 2.74000673061783e-01 2.36115211052070e-01 + 2.90226918370717e-01 2.37236869208110e-01 + 3.06946649593385e-01 2.37961642608874e-01 + 3.24157495235082e-01 2.38100760965162e-01 + 3.41840095169005e-01 2.37744941378091e-01 + 3.59991575578808e-01 2.37085874912214e-01 + 3.78572722909291e-01 2.35662124166498e-01 + 3.97601570515030e-01 2.33909657217884e-01 + 4.17045941396206e-01 2.31611527609804e-01 + 4.36887459877591e-01 2.28775507896640e-01 + 4.57110551645779e-01 2.25393039142808e-01 + 4.77500562687438e-01 2.21532152991484e-01 + 4.98045986283355e-01 2.17089957767898e-01 + 5.18943945591719e-01 2.12153237992339e-01 + 5.40158604865076e-01 2.06620821833843e-01 + 5.61709152880037e-01 2.00663036656115e-01 + 5.83561155582789e-01 1.94212835604329e-01 + 6.05712363627537e-01 1.87316355979470e-01 + 6.28150700503379e-01 1.80008601038694e-01 + 6.50813932385142e-01 1.72131031128422e-01 + 6.73747739165066e-01 1.63919240427144e-01 + 6.96855670314327e-01 1.55129300183976e-01 + 7.20186974564736e-01 1.45990847290388e-01 + 7.43703231915542e-01 1.36459335239714e-01 + 7.67371460256942e-01 1.26508445030746e-01 + 7.91142314551672e-01 1.16082723019247e-01 + 8.15057229103983e-01 1.05359815921843e-01 + 8.39069378083978e-01 9.42866163303158e-02 + 8.63088725121666e-01 8.27135535667870e-02 + 8.87209541825775e-01 7.09271129122314e-02 + 9.11364584609546e-01 5.88247090497486e-02 + 9.35572709644521e-01 4.64753781469346e-02 + 9.59705258308737e-01 3.36031456682403e-02 + 9.83787091325082e-01 2.01066682923067e-02 + 1.00000000000000e+00 1.44711077669299e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF09_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF09_Coords.txt new file mode 100644 index 00000000..05cc3978 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF09_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.284198 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 1.62195843969083e-05 + 9.77407510358482e-01 -6.89879250350199e-03 + 9.50579531463591e-01 -9.59690463596468e-03 + 9.24299887961795e-01 -1.52386252896518e-02 + 8.98410419588860e-01 -2.11832881080788e-02 + 8.72926901501644e-01 -2.89401312101402e-02 + 8.47869982550045e-01 -3.81051033487883e-02 + 8.23259826829256e-01 -4.83025839964879e-02 + 7.99056530928414e-01 -5.90881412538259e-02 + 7.75312979461208e-01 -7.04438973672509e-02 + 7.51959967612238e-01 -8.20265716908182e-02 + 7.29004064520639e-01 -9.37541639211196e-02 + 7.06403946536841e-01 -1.05440040987563e-01 + 6.84103092561771e-01 -1.16856276366701e-01 + 6.62090934936827e-01 -1.27957160088349e-01 + 6.40335157072620e-01 -1.38612918317277e-01 + 6.18813862414738e-01 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6.52388172535362e-02 + 9.06741690193597e-01 5.44871930980383e-02 + 9.31175716009802e-01 4.35617251144147e-02 + 9.55643296907869e-01 3.22181810030390e-02 + 9.80193726831070e-01 2.02005644230895e-02 + 1.00000000000000e+00 5.97937973842799e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF10_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF10_Coords.txt new file mode 100644 index 00000000..67b2a888 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF10_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.267063 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -2.64022008284388e-04 + 9.75314165440816e-01 -4.15659350070438e-03 + 9.48992367308834e-01 -5.72471880436165e-03 + 9.22946273092978e-01 -1.01041592803161e-02 + 8.97096335803002e-01 -1.39118271223155e-02 + 8.71533944214959e-01 -1.96481247334922e-02 + 8.46342823587631e-01 -2.70169397728042e-02 + 8.21577912127079e-01 -3.56330826798859e-02 + 7.97240660024750e-01 -4.50546340754459e-02 + 7.73360302559136e-01 -5.51550915061807e-02 + 7.49923031965700e-01 -6.56884774281976e-02 + 7.26932205273799e-01 -7.65378450546072e-02 + 7.04350857457473e-01 -8.74969127441360e-02 + 6.82139237816719e-01 -9.83606166878958e-02 + 6.60265623585798e-01 -1.09025265250036e-01 + 6.38697836241192e-01 -1.19363744795006e-01 + 6.17409982052701e-01 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3.99515088198649e-01 2.00540833531231e-01 + 4.18408992478983e-01 1.97841982520619e-01 + 4.37699105299070e-01 1.94706186720648e-01 + 4.57374291638498e-01 1.91138375960042e-01 + 4.77076004765730e-01 1.87164876062057e-01 + 4.96818154135232e-01 1.82759035382874e-01 + 5.16926365048355e-01 1.77965105507165e-01 + 5.37388164381310e-01 1.72751492795021e-01 + 5.58202634106987e-01 1.67204287455724e-01 + 5.79354173325763e-01 1.61295554043650e-01 + 6.00836518866323e-01 1.55061267880857e-01 + 6.22638684822529e-01 1.48525360429214e-01 + 6.44739122015505e-01 1.41630459375097e-01 + 6.67139813458437e-01 1.34492460266520e-01 + 6.89809055669925e-01 1.27016018780361e-01 + 7.12743756048402e-01 1.19298582006118e-01 + 7.35924148916157e-01 1.11333080560149e-01 + 7.59332208333489e-01 1.03125420400649e-01 + 7.82943370275724e-01 9.46602525612134e-02 + 8.06751528970084e-01 8.60153882039510e-02 + 8.30733626357925e-01 7.71830433379566e-02 + 8.54857204166652e-01 6.81212653455516e-02 + 8.79128352859622e-01 5.89548199009361e-02 + 9.03516437903694e-01 4.96406990261466e-02 + 9.28022083295763e-01 4.02393127605285e-02 + 9.52597893735403e-01 3.05689361633640e-02 + 9.77237483922068e-01 2.02783577221102e-02 + 1.00000000000000e+00 1.02901147494315e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF11_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF11_Coords.txt new file mode 100644 index 00000000..59fd5cce --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF11_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.254778 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -6.06361831630199e-04 + 9.74278536069251e-01 -1.89392613376563e-03 + 9.48251352965938e-01 -3.80912663943441e-03 + 9.22331013146299e-01 -6.53041529367676e-03 + 8.96506103515080e-01 -8.61512875342120e-03 + 8.70911418779128e-01 -1.25264665439243e-02 + 8.45661797425891e-01 -1.80925531171881e-02 + 8.20828608204991e-01 -2.49958988510343e-02 + 7.96432398643363e-01 -3.28531875559161e-02 + 7.72491557953140e-01 -4.14845304915539e-02 + 7.49017682084612e-01 -5.07152025304428e-02 + 7.26012589733502e-01 -6.04144500502849e-02 + 7.03441213085216e-01 -7.03738496812846e-02 + 6.81271263587267e-01 -8.04157649182165e-02 + 6.59461170372151e-01 -9.03966164928008e-02 + 6.37978589498935e-01 -1.00191143396660e-01 + 6.16795555863364e-01 -1.09693981605727e-01 + 5.95891926942188e-01 -1.18825923201106e-01 + 5.75254548364808e-01 -1.27523168932452e-01 + 5.54883691969404e-01 -1.35757355932793e-01 + 5.34775235825715e-01 -1.43468741716650e-01 + 5.14791769889276e-01 -1.50621850496005e-01 + 4.94827941079654e-01 -1.57233813440814e-01 + 4.75135072237988e-01 -1.63243027794785e-01 + 4.55752196517369e-01 -1.68687550485718e-01 + 4.36670953950430e-01 -1.73493458286081e-01 + 4.17915739337964e-01 -1.77658567133965e-01 + 3.99508443100073e-01 -1.81197030160046e-01 + 3.81469347867722e-01 -1.84127305083245e-01 + 3.63816565471127e-01 -1.86453747741967e-01 + 3.46571403522567e-01 -1.88248905312736e-01 + 3.29748007566493e-01 -1.89474626835771e-01 + 3.13359945540706e-01 -1.90194435953984e-01 + 2.97418761680899e-01 -1.90428555836792e-01 + 2.81934960691538e-01 -1.90187450828064e-01 + 2.66920507901980e-01 -1.89506226836149e-01 + 2.52379874024997e-01 -1.88372435743680e-01 + 2.38312861468895e-01 -1.86827303011689e-01 + 2.24729562393923e-01 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-2.81231557800418e-02 + 2.40591526464724e-03 -2.58389206609114e-02 + 2.08541820453153e-03 -2.36486917648820e-02 + 1.78931769601096e-03 -2.15517635826078e-02 + 1.51955566060929e-03 -1.95430259560952e-02 + 1.27949483807717e-03 -1.76179052706907e-02 + 1.06227835084977e-03 -1.57728520219150e-02 + 8.75008851145894e-04 -1.40048718914509e-02 + 7.20833723055955e-04 -1.23108028286698e-02 + 5.91863407807092e-04 -1.06879377535949e-02 + 4.84809051143090e-04 -9.13384125749992e-03 + 3.84150153887967e-04 -7.64558753567868e-03 + 2.92598631592754e-04 -6.22116585632337e-03 + 2.28616918482540e-04 -4.85854838387978e-03 + 1.69527334506004e-04 -3.55522775495600e-03 + 1.15343437201459e-04 -2.30850438926194e-03 + 6.40853307618280e-05 -1.11626383656354e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 5.76891617590133e-05 1.15929273569901e-03 + 1.28999222654755e-04 2.35379182333715e-03 + 2.12889370492022e-04 3.59777845460044e-03 + 3.08455334816119e-04 4.89737115405152e-03 + 3.99071524053234e-04 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1.13829240593524e-02 5.94252373364938e-02 + 1.28548495441767e-02 6.28948868849671e-02 + 1.44669036856529e-02 6.64773063147728e-02 + 1.62339541964692e-02 7.01705137145486e-02 + 1.81600634216163e-02 7.39696422298139e-02 + 2.02702406772728e-02 7.78654685002289e-02 + 2.25863712090676e-02 8.18526701708310e-02 + 2.51204019963045e-02 8.59290718924292e-02 + 2.78658908122036e-02 9.00891291116383e-02 + 3.08468868400612e-02 9.43251068706000e-02 + 3.40955588797172e-02 9.86280713597437e-02 + 3.76272110159563e-02 1.02989529553042e-01 + 4.14434192349486e-02 1.07403910437394e-01 + 4.55671673414173e-02 1.11852925117302e-01 + 5.00057530705212e-02 1.16321932892218e-01 + 5.47851457166408e-02 1.20799930485210e-01 + 5.99287212401606e-02 1.25268672781196e-01 + 6.54437033528984e-02 1.29703404445447e-01 + 7.13389794535980e-02 1.34089690324119e-01 + 7.76323458169338e-02 1.38413857286720e-01 + 8.43359415875986e-02 1.42664791300242e-01 + 9.14701981711527e-02 1.46807617095263e-01 + 9.90469825544403e-02 1.50821276830237e-01 + 1.07075812570713e-01 1.54693734090661e-01 + 1.15541822958995e-01 1.58416446712199e-01 + 1.24480968999126e-01 1.61962573211125e-01 + 1.33871885621891e-01 1.65318695765066e-01 + 1.43739561132494e-01 1.69952135710290e-01 + 1.54079435151275e-01 1.74387373067812e-01 + 1.64900728796265e-01 1.78148764277955e-01 + 1.76194828998984e-01 1.81415081282843e-01 + 1.87965478572159e-01 1.84252550420798e-01 + 2.00214936270883e-01 1.86686832644915e-01 + 2.12944018620522e-01 1.88726353941826e-01 + 2.26145379708362e-01 1.90393016406948e-01 + 2.39812431346897e-01 1.91686089948856e-01 + 2.53941000347870e-01 1.92599246402474e-01 + 2.68528905092843e-01 1.93161987963255e-01 + 2.83569265491997e-01 1.93335902254531e-01 + 2.99059738521432e-01 1.93122396930199e-01 + 3.14991325380560e-01 1.92536033846166e-01 + 3.31360177843205e-01 1.91538442916722e-01 + 3.48158514112255e-01 1.90148098527275e-01 + 3.65383265607967e-01 1.88405720198178e-01 + 3.83019830172293e-01 1.86235869048758e-01 + 4.01069314511624e-01 1.83702189876028e-01 + 4.19519868509432e-01 1.80781515771706e-01 + 4.38362947154427e-01 1.77484424567366e-01 + 4.57590797728996e-01 1.73819976593022e-01 + 4.77007610767745e-01 1.69800285851103e-01 + 4.96618700372647e-01 1.65425764810728e-01 + 5.16595946907312e-01 1.60724407831146e-01 + 5.36930903129103e-01 1.55691712165099e-01 + 5.57619392098088e-01 1.50376725752821e-01 + 5.78649107158277e-01 1.44769323689177e-01 + 6.00013179942024e-01 1.38898794674575e-01 + 6.21700854747208e-01 1.32782815425195e-01 + 6.43697957855788e-01 1.26406052375068e-01 + 6.65998669367578e-01 1.19832789216483e-01 + 6.88583218439319e-01 1.13028314692417e-01 + 7.11438920287149e-01 1.06036740798250e-01 + 7.34549402992518e-01 9.88649082631487e-02 + 7.57899440310709e-01 9.15292236458133e-02 + 7.81469258658692e-01 8.40306037200766e-02 + 8.05243264703293e-01 7.64075514381593e-02 + 8.29202628945360e-01 6.86696435731776e-02 + 8.53326133984823e-01 6.08151138861190e-02 + 8.77600732894501e-01 5.29050236940674e-02 + 9.02001061213473e-01 4.49248791079078e-02 + 9.26519143444913e-01 3.69319617997908e-02 + 9.51114839848502e-01 2.88383961758660e-02 + 9.75737662078090e-01 2.06840739247021e-02 + 1.00000000000000e+00 1.25843794464830e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF12_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF12_Coords.txt new file mode 100644 index 00000000..4511cd1e --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF12_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250001 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -8.99297851914681e-04 + 9.74055707406337e-01 -2.18231197182105e-03 + 9.48096572495894e-01 -3.41411061023963e-03 + 9.22204366620501e-01 -4.58505219979969e-03 + 8.96385418602361e-01 -5.55615520947839e-03 + 8.70784494659331e-01 -8.15264924489613e-03 + 8.45523117960116e-01 -1.23054777399751e-02 + 8.20676111012135e-01 -1.77935083100358e-02 + 7.96267986893872e-01 -2.43099942558164e-02 + 7.72314891143734e-01 -3.16678871778385e-02 + 7.48833674572419e-01 -3.97295363499704e-02 + 7.25825830235589e-01 -4.83662827826924e-02 + 7.03256671218029e-01 -5.73781505188297e-02 + 6.81095426578380e-01 -6.66103338641311e-02 + 6.59298471626911e-01 -7.58999750445917e-02 + 6.37833402197147e-01 -8.51225466486399e-02 + 6.16671797608682e-01 -9.41687092729788e-02 + 5.95792346957448e-01 -1.02947665179585e-01 + 5.75180968477634e-01 -1.11385420267809e-01 + 5.54837061277546e-01 -1.19439330511854e-01 + 5.34756561215672e-01 -1.27056288535923e-01 + 5.14942200407531e-01 -1.34203734250236e-01 + 4.95402749417922e-01 -1.40864012202764e-01 + 4.76149525856166e-01 -1.47015107922731e-01 + 4.57192324730041e-01 -1.52637755069115e-01 + 4.38539786560989e-01 -1.57707720736193e-01 + 4.20197474441086e-01 -1.62182517177215e-01 + 4.02183143271294e-01 -1.66064691581993e-01 + 3.84518470699951e-01 -1.69380487283873e-01 + 3.67221773583870e-01 -1.72150267344489e-01 + 3.50309713073458e-01 -1.74396789330015e-01 + 3.33796501653124e-01 -1.76137604022864e-01 + 3.17695089865643e-01 -1.77393967414418e-01 + 3.02017119167419e-01 -1.78192862363533e-01 + 2.86772156259859e-01 -1.78540833912021e-01 + 2.71968053037811e-01 -1.78502930517518e-01 + 2.57611664906648e-01 -1.78041106704089e-01 + 2.43708711307942e-01 -1.77200610060995e-01 + 2.30262631492946e-01 -1.76012682591138e-01 + 2.17275672927509e-01 -1.74498711834820e-01 + 2.04748180347900e-01 -1.72683938022583e-01 + 1.92678659012168e-01 -1.70597051815785e-01 + 1.81065642441903e-01 -1.68254563041228e-01 + 1.69905122003014e-01 -1.65680458753517e-01 + 1.59191985974834e-01 -1.62896324607437e-01 + 1.48927509348006e-01 -1.59930355022854e-01 + 1.39104717038827e-01 -1.56783789116353e-01 + 1.29717544889760e-01 -1.53474733078920e-01 + 1.20761451388408e-01 -1.50015449448059e-01 + 1.12226351615633e-01 -1.46429780019040e-01 + 1.04104531839088e-01 -1.42734268333693e-01 + 9.63924570254760e-02 -1.38933675297854e-01 + 8.90832222170918e-02 -1.35040623018826e-01 + 8.21721651846349e-02 -1.31063175468970e-01 + 7.56513630633733e-02 -1.27014118781535e-01 + 6.95115487895842e-02 -1.22908180872060e-01 + 6.37453310812134e-02 -1.18755980730567e-01 + 5.83413021644688e-02 -1.14572841426615e-01 + 5.32855447625140e-02 -1.10376368671079e-01 + 4.85644962965606e-02 -1.06180995807530e-01 + 4.41649173627987e-02 -1.01999544940423e-01 + 4.00688156620742e-02 -9.78490730619561e-02 + 3.62666946212887e-02 -9.37361147509143e-02 + 3.27499756182997e-02 -8.96662189458415e-02 + 2.95085438061577e-02 -8.56460069912596e-02 + 2.65311957978067e-02 -8.16825503685800e-02 + 2.38051051972881e-02 -7.77834969226222e-02 + 2.13172444045643e-02 -7.39557419814804e-02 + 1.90547145877206e-02 -7.02048230748701e-02 + 1.69936313516762e-02 -6.65437240588129e-02 + 1.51055661230311e-02 -6.29843487642342e-02 + 1.33809444939552e-02 -5.95274121676746e-02 + 1.18095056827517e-02 -5.61729393574743e-02 + 1.03757219288988e-02 -5.29242731567652e-02 + 9.06778895548024e-03 -4.97821936104355e-02 + 7.89708934348210e-03 -4.67388458390770e-02 + 6.86762739629727e-03 -4.37873007321140e-02 + 5.95392902103630e-03 -4.09358394579399e-02 + 5.15427996069541e-03 -3.81815959211022e-02 + 4.46252858322884e-03 -3.55214868093499e-02 + 3.88127030572688e-03 -3.29561176817632e-02 + 3.39105707747545e-03 -3.04833854078711e-02 + 2.96717183247041e-03 -2.81080067999491e-02 + 2.59911123713133e-03 -2.58270390948119e-02 + 2.26593496434532e-03 -2.36398810855611e-02 + 1.95057245079241e-03 -2.15459464058071e-02 + 1.65834014361333e-03 -1.95401002096773e-02 + 1.39933351949280e-03 -1.76177148163909e-02 + 1.16855108578612e-03 -1.57752264740965e-02 + 9.69383472722261e-04 -1.40096760149300e-02 + 7.99187348574367e-04 -1.23179338327911e-02 + 6.54425610861769e-04 -1.06972900692834e-02 + 5.40454979671935e-04 -9.14527850550096e-03 + 4.48530163902468e-04 -7.65893595165321e-03 + 3.67998627997102e-04 -6.23630562155651e-03 + 2.90996884868127e-04 -4.87546760752571e-03 + 2.16976283779821e-04 -3.57388327430895e-03 + 1.47366142814586e-04 -2.32882848231901e-03 + 7.78543515982383e-05 -1.13816400082587e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 6.78127517770530e-05 1.13806879874042e-03 + 1.47565943283697e-04 2.32712592022802e-03 + 2.30198285159976e-04 3.56951154667887e-03 + 3.19055240201138e-04 4.86743347754025e-03 + 4.12240668138527e-04 6.22353706135628e-03 + 5.13697434613150e-04 7.63995212338490e-03 + 6.30597521149958e-04 9.11861769878852e-03 + 7.66908908530203e-04 1.06623725976501e-02 + 9.25256842670760e-04 1.22732943614270e-02 + 1.11256152877042e-03 1.39532645705700e-02 + 1.33262866332125e-03 1.57054462643020e-02 + 1.57799503936499e-03 1.75328703986223e-02 + 1.85685160061415e-03 1.94381651623728e-02 + 2.15058105549821e-03 2.14273787730015e-02 + 2.43765140888875e-03 2.35070589711210e-02 + 2.72877038559482e-03 2.56795416515825e-02 + 3.04635067509301e-03 2.79451690349857e-02 + 3.40249455396159e-03 3.03071371482298e-02 + 3.80065016743841e-03 3.27685484987945e-02 + 4.27321730971548e-03 3.53250178426433e-02 + 4.84875125757424e-03 3.79791511252974e-02 + 5.51519325130986e-03 4.07313329985501e-02 + 6.29240997908412e-03 4.35835807327415e-02 + 7.19403708016141e-03 4.65301387243124e-02 + 8.23944450452626e-03 4.95710510239354e-02 + 9.43596749887555e-03 5.27032855836410e-02 + 1.07397581799275e-02 5.59476875359880e-02 + 1.21625182081359e-02 5.93035481965627e-02 + 1.37326457416068e-02 6.27646116430189e-02 + 1.54418319138108e-02 6.63379289616450e-02 + 1.73047536970423e-02 7.00215036166455e-02 + 1.93409124086817e-02 7.38099142863254e-02 + 2.15766352083030e-02 7.76937789888010e-02 + 2.40247623399470e-02 8.16678862422444e-02 + 2.66939996111258e-02 8.57301312773705e-02 + 2.95992775100505e-02 8.98739643525584e-02 + 3.27561233392282e-02 9.40918347407485e-02 + 3.61797152473266e-02 9.83753022210038e-02 + 3.98839307337048e-02 1.02715838067761e-01 + 4.38785893244411e-02 1.07107360382137e-01 + 4.81860293573214e-02 1.11531354359420e-01 + 5.28227834072468e-02 1.15972308943516e-01 + 5.77995250354641e-02 1.20419974649958e-01 + 6.31325141465980e-02 1.24856330563512e-01 + 6.88419819487181e-02 1.29255298497825e-01 + 7.49376378530768e-02 1.33602063922348e-01 + 8.14270361821848e-02 1.37883454732119e-01 + 8.83159723786126e-02 1.42088757637630e-01 + 9.56229806111189e-02 1.46182851763136e-01 + 1.03356804488914e-01 1.50144817252867e-01 + 1.11519818332756e-01 1.53963450441063e-01 + 1.20114354180333e-01 1.57627518689621e-01 + 1.29147285846097e-01 1.61114667892957e-01 + 1.38622392670227e-01 1.64406803564294e-01 + 1.48546697120415e-01 1.67491101076430e-01 + 1.58922601542521e-01 1.70328337196884e-01 + 1.69750469253406e-01 1.72895299872383e-01 + 1.81028727285701e-01 1.75181969815357e-01 + 1.92757118924613e-01 1.77168564278960e-01 + 2.04933816260549e-01 1.78838948215749e-01 + 2.17555461592526e-01 1.80184995573688e-01 + 2.30617465467296e-01 1.81212022700458e-01 + 2.44117205761035e-01 1.81908318363264e-01 + 2.58051161820726e-01 1.82261566882865e-01 + 2.72416276340340e-01 1.82305417547863e-01 + 2.87209054885467e-01 1.81995426373325e-01 + 3.02426119201637e-01 1.81339510533665e-01 + 3.18063704918750e-01 1.80341378478502e-01 + 3.34117190458647e-01 1.78988710332534e-01 + 3.50582887188607e-01 1.77287479137940e-01 + 3.67457411885316e-01 1.75249869525742e-01 + 3.84735241282320e-01 1.72867532494522e-01 + 4.02410840631438e-01 1.70141479775781e-01 + 4.20479861045900e-01 1.67080664184218e-01 + 4.38937337917567e-01 1.63695484138131e-01 + 4.57778369994272e-01 1.59996415385370e-01 + 4.76993987050806e-01 1.55988478484349e-01 + 4.96578866399340e-01 1.51685830097681e-01 + 5.16529791056700e-01 1.47107194833659e-01 + 5.36839132157416e-01 1.42263068183257e-01 + 5.57502062361407e-01 1.37179151139885e-01 + 5.78506947528442e-01 1.31856481715879e-01 + 5.99846801335039e-01 1.26318875145128e-01 + 6.21510917352017e-01 1.20579315267813e-01 + 6.43486642507374e-01 1.14646813491681e-01 + 6.65766554732338e-01 1.08554231709500e-01 + 6.88333354278774e-01 1.02301230862090e-01 + 7.11172372912089e-01 9.59014827558126e-02 + 7.34267939097315e-01 8.93686838710645e-02 + 7.57605408744763e-01 8.27233945350840e-02 + 7.81166012551761e-01 7.59751302935144e-02 + 8.04932152644172e-01 6.91408331092116e-02 + 8.28885866886992e-01 6.22388909791468e-02 + 8.53008300212640e-01 5.52871874665662e-02 + 8.77282284440723e-01 4.83123962886992e-02 + 9.01683465544550e-01 4.13179466502112e-02 + 9.26201800069874e-01 3.43596311850488e-02 + 9.50798227706342e-01 2.73147519752609e-02 + 9.75411025687940e-01 2.02210601345113e-02 + 1.00000000000000e+00 1.30779157393880e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF13_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF13_Coords.txt new file mode 100644 index 00000000..0125507c --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF13_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.90877762153646e-03 + 9.76177095955410e-01 -3.85208958690553e-03 + 9.52277287116538e-01 -3.83111119280944e-03 + 9.28383239307027e-01 -3.82811551770923e-03 + 9.04529994401472e-01 -3.96696457539504e-03 + 8.80840828145205e-01 -5.34019737869113e-03 + 8.57417633200015e-01 -8.18374310592265e-03 + 8.34326859178021e-01 -1.22126401581110e-02 + 8.11595759633889e-01 -1.72101035964300e-02 + 7.89243885521130e-01 -2.30246013841072e-02 + 7.67287548630289e-01 -2.95367087322223e-02 + 7.45732491989749e-01 -3.66415593728245e-02 + 7.24554819149708e-01 -4.41761736694646e-02 + 7.03736195361140e-01 -5.20286394197939e-02 + 6.83244494739171e-01 -6.00573123924261e-02 + 6.63054837090624e-01 -6.81534157746482e-02 + 6.43143898417858e-01 -7.62173001043563e-02 + 6.23494227469507e-01 -8.41652914327959e-02 + 6.04094047547589e-01 -9.19289572385884e-02 + 5.84938808854833e-01 -9.94560415712232e-02 + 5.66022428344779e-01 -1.06695961637198e-01 + 5.47389810776532e-01 -1.13614469364895e-01 + 5.29081352562769e-01 -1.20176980216462e-01 + 5.11024946546101e-01 -1.26368348065976e-01 + 4.93218569544800e-01 -1.32154404950994e-01 + 4.75672046227022e-01 -1.37522625941238e-01 + 4.58379895613815e-01 -1.42417212984863e-01 + 4.41355595903661e-01 -1.46837099566139e-01 + 4.24613086505546e-01 -1.50792954276308e-01 + 4.08167297110225e-01 -1.54303395394699e-01 + 3.92028973923146e-01 -1.57366998915872e-01 + 3.76210015042822e-01 -1.60010907217167e-01 + 3.60719923157279e-01 -1.62235047036860e-01 + 3.45568978559587e-01 -1.64061526227491e-01 + 3.30764205698122e-01 -1.65489425154032e-01 + 3.16311997017383e-01 -1.66575590692259e-01 + 3.02217761394986e-01 -1.67277625747913e-01 + 2.88490723188695e-01 -1.67636352173956e-01 + 2.75132601741012e-01 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2.75539827628001e-02 7.37219853729937e-02 + 3.02502999442799e-02 7.72806708111450e-02 + 3.31152853185371e-02 8.08957175056634e-02 + 3.61597090025231e-02 8.45635874068602e-02 + 3.94018235157987e-02 8.82793767169184e-02 + 4.28617626766180e-02 9.20333961488105e-02 + 4.65457756808214e-02 9.58201884726711e-02 + 5.04601152261955e-02 9.96335158752354e-02 + 5.46213245241059e-02 1.03467699215250e-01 + 5.90365362795236e-02 1.07319070829234e-01 + 6.37121857762988e-02 1.11177318956441e-01 + 6.86573176207854e-02 1.15035401806315e-01 + 7.38810922853281e-02 1.18887132774108e-01 + 7.94004404123226e-02 1.22712074537373e-01 + 8.52284327230626e-02 1.26502381132062e-01 + 9.13676461124212e-02 1.30249244003468e-01 + 9.78274085250955e-02 1.33937033310728e-01 + 1.04626032649977e-01 1.37544441628875e-01 + 1.11769413929706e-01 1.41063831823955e-01 + 1.19259688136687e-01 1.44481579522620e-01 + 1.27097867236153e-01 1.47795780460922e-01 + 1.35296785565090e-01 1.50976072387099e-01 + 1.43861154805552e-01 1.54011410434990e-01 + 1.52789881151373e-01 1.56886707818341e-01 + 1.62089171112070e-01 1.59602598584991e-01 + 1.71754781316711e-01 1.62135324335366e-01 + 1.81796346822162e-01 1.64474533463360e-01 + 1.92213382100991e-01 1.66425363979292e-01 + 2.03009050546195e-01 1.68178912288037e-01 + 2.14180218637347e-01 1.69705078018473e-01 + 2.25727564999561e-01 1.70945370934145e-01 + 2.37648965207326e-01 1.71865540277029e-01 + 2.49941108651580e-01 1.72448620252311e-01 + 2.62599876512358e-01 1.72695694130638e-01 + 2.75622055341312e-01 1.72615098951172e-01 + 2.89006514217906e-01 1.72207177047615e-01 + 3.02749795232816e-01 1.71470103649849e-01 + 3.16849286437346e-01 1.70439370597369e-01 + 3.31302483108853e-01 1.69424774342140e-01 + 3.46105726965195e-01 1.68140432482039e-01 + 3.61257789093933e-01 1.66577432007405e-01 + 3.76754471001010e-01 1.64734882692806e-01 + 3.92593943557866e-01 1.62616780912533e-01 + 4.08772404272451e-01 1.60223262509855e-01 + 4.25287655360067e-01 1.57566274370684e-01 + 4.42133487405743e-01 1.54634663959906e-01 + 4.59307799694892e-01 1.51442933244203e-01 + 4.76807106309904e-01 1.47999683987140e-01 + 4.94627158933230e-01 1.44311657194929e-01 + 5.12822370473813e-01 1.40387948268534e-01 + 5.31382646360085e-01 1.36236308125113e-01 + 5.50249128150191e-01 1.31874675524777e-01 + 5.69414694524883e-01 1.27314121937792e-01 + 5.88874199026108e-01 1.22566985606882e-01 + 6.08618545245910e-01 1.17640995767619e-01 + 6.28640986695080e-01 1.12552045558480e-01 + 6.48931744074941e-01 1.07307462020721e-01 + 6.69481093353748e-01 1.01924988287650e-01 + 6.90282024075574e-01 9.64215377586026e-02 + 7.11320509717455e-01 9.08073616432578e-02 + 7.32584534819389e-01 8.50874326292580e-02 + 7.54060899264128e-01 7.92743217827944e-02 + 7.75736959753760e-01 7.33842784511773e-02 + 7.97597581858509e-01 6.74289362945081e-02 + 8.19629177212279e-01 6.14208725794973e-02 + 8.41817173600272e-01 5.53784629762045e-02 + 8.64144720017884e-01 4.93159955375314e-02 + 8.86598901365336e-01 4.32520815210299e-02 + 9.09160854091841e-01 3.71988721535228e-02 + 9.31820867597258e-01 3.11967366388144e-02 + 9.54545150216031e-01 2.51080100041560e-02 + 9.77282214271235e-01 1.89680903898767e-02 + 1.00000000000000e+00 1.27725024332311e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF14_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF14_Coords.txt new file mode 100644 index 00000000..0e8cdee7 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF14_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -8.07334740112747e-03 + 9.79221200543899e-01 -6.03425302679456e-03 + 9.58276401590868e-01 -4.48600188668470e-03 + 9.37249596414011e-01 -3.48328816766299e-03 + 9.16217026018384e-01 -2.96772689972439e-03 + 8.95271127161916e-01 -3.30786922536192e-03 + 8.74485622936572e-01 -4.99532959252518e-03 + 8.53914947863701e-01 -7.66842174239273e-03 + 8.33590287417539e-01 -1.11944025140524e-02 + 8.13536079423397e-01 -1.54693687661147e-02 + 7.93767861530072e-01 -2.03850293230136e-02 + 7.74297475284363e-01 -2.58670051390440e-02 + 7.55116507909576e-01 -3.17990967062916e-02 + 7.36224469711268e-01 -3.81190940881802e-02 + 7.17605735219894e-01 -4.47231957059536e-02 + 6.99246220737501e-01 -5.15250093631793e-02 + 6.81129915784949e-01 -5.84408057021431e-02 + 6.63244907650762e-01 -6.54024930904345e-02 + 6.45582727402024e-01 -7.23544273766168e-02 + 6.28133158892752e-01 -7.92378276698723e-02 + 6.10887222053294e-01 -8.60030799733642e-02 + 5.93870978386956e-01 -9.26124539968124e-02 + 5.77105211283826e-01 -9.90235215725858e-02 + 5.60534655930499e-01 -1.05212997679798e-01 + 5.44155709491168e-01 -1.11151843455848e-01 + 5.27970929841038e-01 -1.16821361726290e-01 + 5.11968863797175e-01 -1.22165480718227e-01 + 4.96158991064346e-01 -1.27183275763906e-01 + 4.80543386723467e-01 -1.31859964360396e-01 + 4.65131989286139e-01 -1.36204242521235e-01 + 4.49929469215702e-01 -1.40203347834267e-01 + 4.34944347851167e-01 -1.43872151302930e-01 + 4.20181485878933e-01 -1.47199731605473e-01 + 4.05649144244415e-01 -1.50197795203218e-01 + 3.91351176424123e-01 -1.52856219387145e-01 + 3.77294015446200e-01 -1.55206451007822e-01 + 3.63479738318255e-01 -1.57210423299989e-01 + 3.49919502444129e-01 -1.58899631007322e-01 + 3.36616022215246e-01 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-5.34247492034163e-02 + 1.47790669382181e-02 -4.98766349049358e-02 + 1.28406771478420e-02 -4.63677910308392e-02 + 1.10427125043029e-02 -4.29014670346303e-02 + 9.38018305897801e-03 -3.94808026390514e-02 + 7.87007689212147e-03 -3.61054963151586e-02 + 6.49787574483746e-03 -3.27756736717481e-02 + 5.29449824963774e-03 -2.94901370487684e-02 + 4.23510008626491e-03 -2.62497227090602e-02 + 3.32948275108824e-03 -2.30654495585963e-02 + 2.55676087926568e-03 -1.99373468861916e-02 + 1.93301398383811e-03 -1.68738856235686e-02 + 1.41336434125244e-03 -1.38752546647408e-02 + 9.59565805648218e-04 -1.09546456906559e-02 + 5.57550777445461e-04 -8.10914997122945e-03 + 2.97369527194442e-04 -5.33638511455700e-03 + 1.05092610307520e-04 -2.63267378705458e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 9.55567127353597e-05 2.62159030229867e-03 + 2.98415981526065e-04 5.32187329611126e-03 + 5.58963178979173e-04 8.09117878761504e-03 + 9.50743688766724e-04 1.09316435327940e-02 + 1.39483046102671e-03 1.38472305963159e-02 + 1.89605375643053e-03 1.68408051499943e-02 + 2.47743496809607e-03 1.99066668803368e-02 + 3.15705504981302e-03 2.30473802965293e-02 + 3.95396258443797e-03 2.62489321137118e-02 + 4.90966800227364e-03 2.95083060104062e-02 + 6.01732699926503e-03 3.28144611520736e-02 + 7.29878278121537e-03 3.61643223152113e-02 + 8.71775090763030e-03 3.95618349948329e-02 + 1.02768390461423e-02 4.30082745506948e-02 + 1.19542835779178e-02 4.65049840738280e-02 + 1.37660735218386e-02 5.00484247348741e-02 + 1.57261925461139e-02 5.36344556756830e-02 + 1.78379343589320e-02 5.72580990875103e-02 + 2.01081376384622e-02 6.09160827342359e-02 + 2.25541998569176e-02 6.45986486726600e-02 + 2.51909930226753e-02 6.83016586300093e-02 + 2.80174362842042e-02 7.20223532558272e-02 + 3.10369095528759e-02 7.57602850426688e-02 + 3.42592751817078e-02 7.94995398292520e-02 + 3.76917389970838e-02 8.32397989580815e-02 + 4.13377178168780e-02 8.69771633659212e-02 + 4.51834652692616e-02 9.07064903394664e-02 + 4.92294692994139e-02 9.44249906041134e-02 + 5.34901624008167e-02 9.81237593020423e-02 + 5.79625758049088e-02 1.01798686508183e-01 + 6.26519723823795e-02 1.05444022187550e-01 + 6.75667093990260e-02 1.09055605231701e-01 + 7.27173460390111e-02 1.12623305408261e-01 + 7.81054229353040e-02 1.16141312838526e-01 + 8.37353736611478e-02 1.19597459010706e-01 + 8.96148506174161e-02 1.22987314176471e-01 + 9.57434173326257e-02 1.26312782630787e-01 + 1.02123872111929e-01 1.29560866993600e-01 + 1.08759070540133e-01 1.32726659148873e-01 + 1.15652909023735e-01 1.35803822311014e-01 + 1.22814898880055e-01 1.38769160480619e-01 + 1.30248312878360e-01 1.41625826790262e-01 + 1.37952119160829e-01 1.44367080243205e-01 + 1.45929421185843e-01 1.46980722029795e-01 + 1.54188974871623e-01 1.49452290676138e-01 + 1.62730776625850e-01 1.51784448266146e-01 + 1.71554543533328e-01 1.53962921382450e-01 + 1.80657738055108e-01 1.55998446174920e-01 + 1.90046005272108e-01 1.57867488786970e-01 + 1.99719900707754e-01 1.59573174399796e-01 + 2.09677081941992e-01 1.61094844055895e-01 + 2.19920331715425e-01 1.62450160193982e-01 + 2.30444639108594e-01 1.63613348744482e-01 + 2.41254910947225e-01 1.64585169319622e-01 + 2.52349268622484e-01 1.65661492597062e-01 + 2.63728332369411e-01 1.66615987835985e-01 + 2.75388576827329e-01 1.67214313405789e-01 + 2.87330237434036e-01 1.67438497932802e-01 + 2.99550601211257e-01 1.67281149315567e-01 + 3.12046369103180e-01 1.66745200004450e-01 + 3.24814518081560e-01 1.65851159556216e-01 + 3.37852379098881e-01 1.64617075526103e-01 + 3.51158899179799e-01 1.63061672052833e-01 + 3.64730380997744e-01 1.61196317356998e-01 + 3.78565323114399e-01 1.59055554299456e-01 + 3.92660884442849e-01 1.57290559237541e-01 + 4.07013562849287e-01 1.55335288522997e-01 + 4.21623042634860e-01 1.53174219521817e-01 + 4.36486154332345e-01 1.50811035733740e-01 + 4.51601608219310e-01 1.48252581018077e-01 + 4.66965183091982e-01 1.45494985385807e-01 + 4.82574701407707e-01 1.42548984855696e-01 + 4.98426491448941e-01 1.39413973553154e-01 + 5.14517752353766e-01 1.36098188226949e-01 + 5.30845249617679e-01 1.32607833013793e-01 + 5.47404182012442e-01 1.28943941449471e-01 + 5.64234122265171e-01 1.25124266848195e-01 + 5.81324152134668e-01 1.21141864667106e-01 + 5.98634521691505e-01 1.17017578674898e-01 + 6.16158837812567e-01 1.12756929106355e-01 + 6.33891496205559e-01 1.08363822198320e-01 + 6.51827041881908e-01 1.03850480257554e-01 + 6.69959072516104e-01 9.92242630318279e-02 + 6.88279139184040e-01 9.44867269543307e-02 + 7.06781720669086e-01 8.96575051098235e-02 + 7.25460397362862e-01 8.47447902935426e-02 + 7.44305839320801e-01 7.97592135386944e-02 + 7.63309837923549e-01 7.47064611684110e-02 + 7.82462739311484e-01 6.95948278249936e-02 + 8.01754771137058e-01 6.44330951982709e-02 + 8.21176014681886e-01 5.92324206564670e-02 + 8.40718635263391e-01 5.40082149246081e-02 + 8.60372924903524e-01 4.87753362998312e-02 + 8.80124908010382e-01 4.35353451878232e-02 + 8.99967772961271e-01 3.83096141062618e-02 + 9.19890534609507e-01 3.31146158959137e-02 + 9.39883960266685e-01 2.79691489091252e-02 + 9.59921818368150e-01 2.27772902091126e-02 + 9.79967309603052e-01 1.75595788635621e-02 + 1.00000000000000e+00 1.23146665498868e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF15_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF15_Coords.txt new file mode 100644 index 00000000..d3d9f2fa --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF15_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -1.10509575423538e-02 + 9.81411690826682e-01 -7.57971372427505e-03 + 9.62593270995096e-01 -4.92654587127468e-03 + 9.43629688990319e-01 -3.19635258549884e-03 + 9.24626832070457e-01 -2.30138153875055e-03 + 9.05654945738084e-01 -2.09475830937593e-03 + 8.86767482701158e-01 -3.04025558509015e-03 + 8.68010231608718e-01 -4.82957516185432e-03 + 8.49417207283124e-01 -7.38484241818010e-03 + 8.31016364066570e-01 -1.06360119301930e-02 + 8.12822682547506e-01 -1.44809349847565e-02 + 7.94852392671663e-01 -1.88667158279844e-02 + 7.77108223472522e-01 -2.37100321442376e-02 + 7.59602526279175e-01 -2.89829645033655e-02 + 7.42331549064133e-01 -3.46098634839686e-02 + 7.25288977119364e-01 -4.05204175569251e-02 + 7.08464062659816e-01 -4.66426040685526e-02 + 6.91848878421112e-01 -5.29202112398719e-02 + 6.75437335686597e-01 -5.93073955668692e-02 + 6.59215140893944e-01 -6.57415853949234e-02 + 6.43171229320706e-01 -7.21735336027545e-02 + 6.27308226456623e-01 -7.85628722356951e-02 + 6.11624713487422e-01 -8.48635760226628e-02 + 5.96094539920748e-01 -9.10442639047107e-02 + 5.80714880183991e-01 -9.70828872714430e-02 + 5.65481947225649e-01 -1.02953448564325e-01 + 5.50381219396596e-01 -1.08602021926968e-01 + 5.35419565272026e-01 -1.14028447746342e-01 + 5.20590427913323e-01 -1.19199243257144e-01 + 5.05900137980011e-01 -1.24115041319193e-01 + 4.91349294093509e-01 -1.28757827845388e-01 + 4.76943980791057e-01 -1.33130403509631e-01 + 4.62685756464561e-01 -1.37216499816543e-01 + 4.48581420734730e-01 -1.41019914657937e-01 + 4.34632604662850e-01 -1.44524090636448e-01 + 4.20846036166405e-01 -1.47740500742434e-01 + 4.07221238353771e-01 -1.50635510220325e-01 + 3.93770374269343e-01 -1.53233531715719e-01 + 3.80497305313331e-01 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-6.41549819671272e-02 + 1.99013660083038e-02 -6.00695207200590e-02 + 1.72850788874385e-02 -5.60002019537108e-02 + 1.48626645326118e-02 -5.19519017368173e-02 + 1.26240169385869e-02 -4.79312687108058e-02 + 1.05875607745008e-02 -4.39398358989068e-02 + 8.73433299474148e-03 -3.99792934225952e-02 + 7.10774510080775e-03 -3.60491906063883e-02 + 5.67481526323844e-03 -3.21520454802931e-02 + 4.45004076252820e-03 -2.83046987771536e-02 + 3.39950311639580e-03 -2.45082380332127e-02 + 2.54832756291068e-03 -2.07759829409580e-02 + 1.84009183591997e-03 -1.71090322906018e-02 + 1.22940616128262e-03 -1.35269859869500e-02 + 6.91637176855277e-04 -1.00267783584981e-02 + 3.54078146575947e-04 -6.60617193597537e-03 + 1.13845813955877e-04 -3.26083713812033e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 1.05197958660838e-04 3.25536855273048e-03 + 3.58331849259044e-04 6.59742678863812e-03 + 6.94566901935779e-04 1.00142387509855e-02 + 1.21627365955504e-03 1.35088350454241e-02 + 1.80859442021047e-03 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5.38846096800813e-01 1.29336404307583e-01 + 5.54183001884026e-01 1.25939291250943e-01 + 5.69692561557026e-01 1.22419546752540e-01 + 5.85369391309433e-01 1.18774054003556e-01 + 6.01229218670740e-01 1.15027146197698e-01 + 6.17261282389790e-01 1.11160619278953e-01 + 6.33451897803230e-01 1.07197909270273e-01 + 6.49795195786550e-01 1.03139748134717e-01 + 6.66285242597059e-01 9.89853115090349e-02 + 6.82919203554898e-01 9.47494190976470e-02 + 6.99690923989396e-01 9.04336429025070e-02 + 7.16592912293283e-01 8.60356789560214e-02 + 7.33622671530269e-01 8.15751962475538e-02 + 7.50774207256676e-01 7.70558751331495e-02 + 7.68041569112651e-01 7.24867760706181e-02 + 7.85419287822119e-01 6.78757411633822e-02 + 8.02900261357254e-01 6.32276565982537e-02 + 8.20476783261702e-01 5.85457709779441e-02 + 8.38142687961821e-01 5.38404614301608e-02 + 8.55894281036140e-01 4.91303096274833e-02 + 8.73725354735666e-01 4.44272073052611e-02 + 8.91624002570722e-01 3.97226144336362e-02 + 9.09587804885732e-01 3.50416738573172e-02 + 9.27611445710978e-01 3.04029484428038e-02 + 9.45686036255908e-01 2.58097842951588e-02 + 9.63790785086802e-01 2.11950192782819e-02 + 9.81899462412430e-01 1.65697747312077e-02 + 1.00000000000000e+00 1.19344536950897e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF16_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF16_Coords.txt new file mode 100644 index 00000000..50af0d34 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF16_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -1.24252640800748e-02 + 9.82425475701935e-01 -8.13509426619932e-03 + 9.64591169339978e-01 -4.87734430030055e-03 + 9.46582471482630e-01 -2.81411840337627e-03 + 9.28518990025422e-01 -1.80640395947902e-03 + 9.10460700094831e-01 -1.58235815617821e-03 + 8.92451673024753e-01 -2.20215711161437e-03 + 8.74533696052007e-01 -3.60052209291324e-03 + 8.56742093454814e-01 -5.72386945519578e-03 + 8.39106447061078e-01 -8.51774183837510e-03 + 8.21641479645111e-01 -1.18824656751187e-02 + 8.04365452155706e-01 -1.57749984659010e-02 + 7.87286250188198e-01 -2.01270794263903e-02 + 7.70422168049626e-01 -2.49263691477237e-02 + 7.53774948882267e-01 -3.01104285576322e-02 + 7.37341873558742e-01 -3.56163831485470e-02 + 7.21114629931218e-01 -4.13776776099346e-02 + 7.05087135247494e-01 -4.73437295122691e-02 + 6.89254402383221e-01 -5.34733489013033e-02 + 6.73600250699443e-01 -5.97023876255703e-02 + 6.58112650671682e-01 -6.59817033961564e-02 + 6.42781438555545e-01 -7.22696815682527e-02 + 6.27593328972990e-01 -7.85190347480942e-02 + 6.12538988806551e-01 -8.46941944361605e-02 + 5.97616328690040e-01 -9.07769961993379e-02 + 5.82818405573326e-01 -9.67375014161532e-02 + 5.68129519439464e-01 -1.02523238235982e-01 + 5.53555382749166e-01 -1.08134531532468e-01 + 5.39085424948161e-01 -1.13529167900029e-01 + 5.24724303737483e-01 -1.18703866870826e-01 + 5.10470792285467e-01 -1.23638755686121e-01 + 4.96329845983840e-01 -1.28330411405035e-01 + 4.82301502361614e-01 -1.32760574472246e-01 + 4.68391883101538e-01 -1.36929299219655e-01 + 4.54601602382362e-01 -1.40817087120938e-01 + 4.40937576860884e-01 -1.44425833341921e-01 + 4.27398116918708e-01 -1.47724213168402e-01 + 4.13995775223519e-01 -1.50733288697601e-01 + 4.00735028800926e-01 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3.35859971674524e-02 + 9.31184774914660e-01 2.91926669736630e-02 + 9.48371305818242e-01 2.48424981540045e-02 + 9.65581388758071e-01 2.04643678442921e-02 + 9.82793685641916e-01 1.60706837689086e-02 + 1.00000000000000e+00 1.16593285865521e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF17_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF17_Coords.txt new file mode 100644 index 00000000..48f6b1f3 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF17_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -1.22296732978971e-02 + 9.81809231997450e-01 -7.66325101842351e-03 + 9.63362020906993e-01 -4.26138903321795e-03 + 9.44746882275587e-01 -2.24733614559064e-03 + 9.26083982102653e-01 -1.38644381886032e-03 + 9.07437793637814e-01 -1.53384239700012e-03 + 8.88856404100716e-01 -2.32693033767316e-03 + 8.70383681457240e-01 -3.92705639126025e-03 + 8.52056691131542e-01 -6.27418411468357e-03 + 8.33906603147679e-01 -9.31215046334780e-03 + 8.15950523038870e-01 -1.29428641300523e-02 + 7.98204200093546e-01 -1.71077183616288e-02 + 7.80674665832591e-01 -2.17331052675344e-02 + 7.63378191963654e-01 -2.67977731219143e-02 + 7.46314515499711e-01 -3.22328632370932e-02 + 7.29478641179161e-01 -3.79691530756852e-02 + 7.12860910320368e-01 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3.39379729071236e-02 + 9.28868179178930e-01 2.94209452862480e-02 + 9.46626564710179e-01 2.49493364505803e-02 + 9.64414839745242e-01 2.04458435480200e-02 + 9.82209801121977e-01 1.59240487172577e-02 + 1.00000000000000e+00 1.13821920044181e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF18_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF18_Coords.txt new file mode 100644 index 00000000..494d4335 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF18_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -1.16632865296421e-02 + 9.80217654328904e-01 -6.92509062408520e-03 + 9.60188302276238e-01 -3.47720169982583e-03 + 9.40008342543793e-01 -1.62141042692285e-03 + 9.19798890257740e-01 -9.84799370916085e-04 + 8.99636132540208e-01 -1.42658986873376e-03 + 8.79578621787504e-01 -2.66830892914488e-03 + 8.59675619332631e-01 -4.79121439832610e-03 + 8.39968547108665e-01 -7.71816230647970e-03 + 8.20492534390534e-01 -1.13881558100171e-02 + 8.01270717529288e-01 -1.57070253661491e-02 + 7.82312429580785e-01 -2.05764974766374e-02 + 7.63622370079569e-01 -2.59089460778903e-02 + 7.45211498988559e-01 -3.16600753977219e-02 + 7.27074298261763e-01 -3.77443546888712e-02 + 7.09199899054353e-01 -4.40762674869390e-02 + 6.91575157567226e-01 -5.05758330830263e-02 + 6.74188963501973e-01 -5.71775559506585e-02 + 6.57030352285490e-01 -6.38218095061332e-02 + 6.40084081491944e-01 -7.04420266390534e-02 + 6.23339557323550e-01 -7.69862248432273e-02 + 6.06787128885386e-01 -8.34062094890199e-02 + 5.90419282702000e-01 -8.96609914654253e-02 + 5.74231528259348e-01 -9.57173463476151e-02 + 5.58224657673924e-01 -1.01554962969757e-01 + 5.42397362574000e-01 -1.07149396358289e-01 + 5.26743502195508e-01 -1.12465677563980e-01 + 5.11271756957334e-01 -1.17506597410144e-01 + 4.95978715201395e-01 -1.22243265855024e-01 + 4.80871678879433e-01 -1.26676107420163e-01 + 4.65954449488553e-01 -1.30799259244738e-01 + 4.51233469825178e-01 -1.34611231534369e-01 + 4.36712467656939e-01 -1.38107692620167e-01 + 4.22398369061556e-01 -1.41293244614854e-01 + 4.08294288176469e-01 -1.44162751378535e-01 + 3.94406752726309e-01 -1.46725919933101e-01 + 3.80736171500234e-01 -1.48966261238432e-01 + 3.67292537958174e-01 -1.50893958601297e-01 + 3.54079354080868e-01 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-5.63066718745816e-02 + 1.69854303472378e-02 -5.26541425272748e-02 + 1.47151058422611e-02 -4.90249539685495e-02 + 1.26204707975494e-02 -4.54247856872051e-02 + 1.06844600893296e-02 -4.18610018263988e-02 + 8.92572101090407e-03 -3.83331838313589e-02 + 7.34344739742936e-03 -3.48377906513379e-02 + 5.96185450933529e-03 -3.13777109356842e-02 + 4.74970502747944e-03 -2.79556186151972e-02 + 3.72553821482971e-03 -2.45846939956754e-02 + 2.85254518581349e-03 -2.12656749283929e-02 + 2.14467948559800e-03 -1.80104156369561e-02 + 1.55686984724083e-03 -1.48192629888907e-02 + 1.05161621044168e-03 -1.17073749587869e-02 + 6.04684511656445e-04 -8.67219194455909e-03 + 3.17558002523636e-04 -5.71139385374425e-03 + 1.09603574592077e-04 -2.82105853016805e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 1.04133011985657e-04 2.80019482937380e-03 + 3.20781607272749e-04 5.68802423881039e-03 + 6.05657737636481e-04 8.64551523414676e-03 + 1.03870062611886e-03 1.16757579775280e-02 + 1.52703821225340e-03 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1.53058588083530e-01 + 2.28047793741785e-01 1.53996899815121e-01 + 2.38483221681258e-01 1.54778972526587e-01 + 2.49171299834269e-01 1.55378972885210e-01 + 2.60111419236226e-01 1.55961702005729e-01 + 2.71304764225112e-01 1.55815126187117e-01 + 2.82750754179475e-01 1.55353269262063e-01 + 2.94448827679890e-01 1.54897002790587e-01 + 3.06398756362994e-01 1.54427745277158e-01 + 3.18599496489687e-01 1.53910327183813e-01 + 3.31049496710481e-01 1.53310934064898e-01 + 3.43747917939376e-01 1.52613186174334e-01 + 3.56693331415869e-01 1.51791317103658e-01 + 3.69884979931269e-01 1.50827218545616e-01 + 3.83320140088490e-01 1.49679120059038e-01 + 3.96998543160869e-01 1.48356344913779e-01 + 4.10917417268813e-01 1.46574702279958e-01 + 4.25074213588026e-01 1.44585799260896e-01 + 4.39468758018075e-01 1.42425706690933e-01 + 4.54099191912527e-01 1.40096936199139e-01 + 4.68963893395827e-01 1.37603642301520e-01 + 4.84059017671957e-01 1.34943731355758e-01 + 4.99381428649330e-01 1.32119947861434e-01 + 5.14929487968173e-01 1.29140227434892e-01 + 5.30699520004976e-01 1.26009865620594e-01 + 5.46687610562902e-01 1.22730744424277e-01 + 5.62887978434513e-01 1.19299537728892e-01 + 5.79299936312816e-01 1.15735359991450e-01 + 5.95914619547052e-01 1.12026818450527e-01 + 6.12730709236635e-01 1.08193835180151e-01 + 6.29743115305241e-01 1.04243942733819e-01 + 6.46943985330232e-01 1.00172688420283e-01 + 6.64328941897631e-01 9.59920179986369e-02 + 6.81891154735795e-01 9.17066524220465e-02 + 6.99621625137081e-01 8.73138166385594e-02 + 7.17516439128198e-01 8.28326480971229e-02 + 7.35566698100536e-01 7.82640172512667e-02 + 7.53765329156961e-01 7.36179318289522e-02 + 7.72104984951822e-01 6.89049292301415e-02 + 7.90576506135902e-01 6.41298775103396e-02 + 8.09171494303623e-01 5.93024873868261e-02 + 8.27882121516277e-01 5.44356425302492e-02 + 8.46702517631436e-01 4.95509174769936e-02 + 8.65622909509902e-01 4.46562074349216e-02 + 8.84631945592956e-01 3.97550678929255e-02 + 9.03724711163877e-01 3.48766374686173e-02 + 9.22893082456990e-01 3.00389238712883e-02 + 9.42126629336644e-01 2.52524243263971e-02 + 9.61406305100774e-01 2.04763805013702e-02 + 9.80704028333917e-01 1.57106771972442e-02 + 1.00000000000000e+00 1.09645280246108e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF19_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF19_Coords.txt new file mode 100644 index 00000000..cfa685c2 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF19_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -1.09393020671112e-02 + 9.78333496951182e-01 -6.09819736643714e-03 + 9.56431158976776e-01 -2.65453624834099e-03 + 9.34398717093692e-01 -1.00094576310997e-03 + 9.12358410032814e-01 -6.01121712902224e-04 + 8.90400292149856e-01 -1.29742623431100e-03 + 8.68595304831126e-01 -3.07024826935875e-03 + 8.46999094239379e-01 -5.81203568962472e-03 + 8.25658239673608e-01 -9.42539212210090e-03 + 8.04612557488666e-01 -1.38435983269780e-02 + 7.83892323498624e-01 -1.89771274637964e-02 + 7.63499275030790e-01 -2.46807473518411e-02 + 7.43435350944336e-01 -3.08502367938405e-02 + 7.23705222999466e-01 -3.74140197844376e-02 + 7.04297152053772e-01 -4.42668286922150e-02 + 6.85193315938445e-01 -5.13038578132970e-02 + 6.66376445067804e-01 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3.59900516032138e-02 + 9.15819583755837e-01 3.07727003291269e-02 + 9.36799470881938e-01 2.56134237186330e-02 + 9.57844711558385e-01 2.05154769117794e-02 + 9.78921449347125e-01 1.54616216932341e-02 + 1.00000000000000e+00 1.04746693688942e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF20_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF20_Coords.txt new file mode 100644 index 00000000..4d5ac3ae --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF20_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -1.01629406069420e-02 + 9.76564055555559e-01 -5.27635803339109e-03 + 9.52902767472989e-01 -1.86644206570412e-03 + 9.29130630890963e-01 -4.17973315924122e-04 + 9.05370939734970e-01 -2.29089713392072e-04 + 8.81726771294709e-01 -1.17216790376347e-03 + 8.58280701649009e-01 -3.44375697375845e-03 + 8.35094373053208e-01 -6.76674602622409e-03 + 8.12219208168558e-01 -1.10247193424094e-02 + 7.89699425059321e-01 -1.61455836915237e-02 + 7.67572004319938e-01 -2.20441722668217e-02 + 7.45831550011316e-01 -2.85311532610704e-02 + 7.24477408399593e-01 -3.54867207297548e-02 + 7.03508345896347e-01 -4.28136793777355e-02 + 6.82906781031105e-01 -5.03882263597857e-02 + 6.62648361660741e-01 -5.80874411482768e-02 + 6.42711943609450e-01 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4.44442583645683e-01 1.36311193023964e-01 + 4.61498654081415e-01 1.33679695244267e-01 + 4.78896412812820e-01 1.30817532351858e-01 + 4.96629937243072e-01 1.27724249665593e-01 + 5.14694278337904e-01 1.24405187040223e-01 + 5.33083322517832e-01 1.20869065989101e-01 + 5.51791921140529e-01 1.17127863724620e-01 + 5.70815861312387e-01 1.13204253715040e-01 + 5.90144388901980e-01 1.09091023302907e-01 + 6.09768567816414e-01 1.04793597428767e-01 + 6.29680265528769e-01 1.00326224467597e-01 + 6.49867266026613e-01 9.56882359317000e-02 + 6.70320991796415e-01 9.08983041609065e-02 + 6.91027439521691e-01 8.59555770060733e-02 + 7.11975083089197e-01 8.08734401039727e-02 + 7.33151373098203e-01 7.56646593401528e-02 + 7.54541797950800e-01 7.03368113684905e-02 + 7.76135227583435e-01 6.49145563683423e-02 + 7.97918204786827e-01 5.94156469528838e-02 + 8.19878087177515e-01 5.38637608640574e-02 + 8.41996537350120e-01 4.82626518218661e-02 + 8.64261520472198e-01 4.26438717559159e-02 + 8.86660630181438e-01 3.70396348331895e-02 + 9.09176751494747e-01 3.14657599329256e-02 + 9.31796653812487e-01 2.59564026025220e-02 + 9.54499963862254e-01 2.05416793916086e-02 + 9.77247401792770e-01 1.51928007971372e-02 + 1.00000000000000e+00 9.94263213662223e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF21_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF21_Coords.txt new file mode 100644 index 00000000..f77c42b9 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF21_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -9.42412799643962e-03 + 9.75329853741237e-01 -4.55562302984154e-03 + 9.50441681614827e-01 -1.20075060044008e-03 + 9.25456091815809e-01 8.90361527071166e-05 + 9.00497114277709e-01 1.35652908829840e-04 + 8.75676909907685e-01 -1.07670175435165e-03 + 8.51086170090705e-01 -3.69618546554730e-03 + 8.26790719412394e-01 -7.42456805674336e-03 + 8.02845358824188e-01 -1.21321676388136e-02 + 7.79297376623554e-01 -1.77431425723253e-02 + 7.56188430051543e-01 -2.41753672145602e-02 + 7.33508147649464e-01 -3.12087498590349e-02 + 7.11254067325731e-01 -3.87126140552249e-02 + 6.89420836456379e-01 -4.65718948153249e-02 + 6.67986798492830e-01 -5.46498608102546e-02 + 6.46923046574195e-01 -6.28109562545029e-02 + 6.26205733962059e-01 -7.09454982411323e-02 + 6.05812633676340e-01 -7.89550095837847e-02 + 5.85719596036303e-01 -8.67391575759325e-02 + 5.65913498323342e-01 -9.42260960195752e-02 + 5.46386934179133e-01 -1.01357590615292e-01 + 5.27131783347551e-01 -1.08071004922419e-01 + 5.08153603049962e-01 -1.14339239862498e-01 + 4.89458018433735e-01 -1.20134357827350e-01 + 4.71052135142369e-01 -1.25431200973852e-01 + 4.52947138956048e-01 -1.30217536030444e-01 + 4.35157954465966e-01 -1.34496858511634e-01 + 4.17699825926991e-01 -1.38277369302885e-01 + 4.00585211986335e-01 -1.41559751966697e-01 + 3.83827282066409e-01 -1.44352700697479e-01 + 3.67440954667878e-01 -1.46681226456357e-01 + 3.51435978570786e-01 -1.48548284477431e-01 + 3.35824246013088e-01 -1.49980241588510e-01 + 3.20614472945683e-01 -1.50991817692829e-01 + 3.05815304053432e-01 -1.51609565414580e-01 + 2.91432404978324e-01 -1.51860666268209e-01 + 2.77470837817852e-01 -1.51761204493462e-01 + 2.63934954391910e-01 -1.51297524706721e-01 + 2.50826091946355e-01 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-2.79436223780135e-02 + 5.28891663995497e-03 -2.57982250682069e-02 + 4.47902608440423e-03 -2.37158741595429e-02 + 3.74947008799864e-03 -2.17023384473732e-02 + 3.07324750782609e-03 -1.97629355238332e-02 + 2.46820745279427e-03 -1.78910594319472e-02 + 1.97813659861554e-03 -1.60700439190365e-02 + 1.57201164732671e-03 -1.43093546933737e-02 + 1.23066420520135e-03 -1.26102732698391e-02 + 9.76807500162775e-04 -1.09719177998627e-02 + 7.80970958473876e-04 -9.39316464869130e-03 + 6.23385034561832e-04 -7.87763983329989e-03 + 4.95480132103175e-04 -6.42309673391595e-03 + 3.83737677651824e-04 -5.02830642196525e-03 + 2.76337472951990e-04 -3.69198480915191e-03 + 1.79582180841092e-04 -2.41148044821756e-03 + 8.93066802273239e-05 -1.18444075874648e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 8.87155415365147e-05 1.16543652634416e-03 + 1.76856954298385e-04 2.39138857044313e-03 + 2.70586320936143e-04 3.67000403318993e-03 + 3.74265558963138e-04 5.00346088038491e-03 + 4.80904972227802e-04 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2.22704454466001e-02 5.59909355367613e-02 + 2.46482270643390e-02 5.89192644161555e-02 + 2.72046905537579e-02 6.19008882746400e-02 + 2.99478238943702e-02 6.49332605483564e-02 + 3.28867141541042e-02 6.80122042564707e-02 + 3.60247252019180e-02 7.11383290361901e-02 + 3.93723806831674e-02 7.43062629696090e-02 + 4.29383788105744e-02 7.75121784767503e-02 + 4.67300479284695e-02 8.07534138286789e-02 + 5.07578936078280e-02 8.40238263856248e-02 + 5.50296689334694e-02 8.73189267140286e-02 + 5.95573647239966e-02 9.06293037902330e-02 + 6.43509771567079e-02 9.39476171559126e-02 + 6.94186935238437e-02 9.72682712290645e-02 + 7.47680797353169e-02 1.00586826715747e-01 + 8.04092216594491e-02 1.03894513317287e-01 + 8.63513992620265e-02 1.07182865933725e-01 + 9.26084622225283e-02 1.10433602563920e-01 + 9.91855085003989e-02 1.13644501385217e-01 + 1.06093340292706e-01 1.16801032155078e-01 + 1.13343734971317e-01 1.19885345927272e-01 + 1.20943353847432e-01 1.22889480896982e-01 + 1.28899205788087e-01 1.25802810631623e-01 + 1.37221323455695e-01 1.28605953502730e-01 + 1.45914808078555e-01 1.31291271512215e-01 + 1.54988447006057e-01 1.33837489255144e-01 + 1.64446495421741e-01 1.36390122612035e-01 + 1.74295828781056e-01 1.38825110742499e-01 + 1.84540801381575e-01 1.41034176702179e-01 + 1.95186170070837e-01 1.43013605956377e-01 + 2.06233396596869e-01 1.44752020162416e-01 + 2.17685522914215e-01 1.46226596825883e-01 + 2.29543838435437e-01 1.47421487783478e-01 + 2.41808760543078e-01 1.48331474094163e-01 + 2.54480977227042e-01 1.48945394853222e-01 + 2.67561143490204e-01 1.49252656392873e-01 + 2.81049386480181e-01 1.49213956539601e-01 + 2.94945351409727e-01 1.48864228524309e-01 + 3.09248004158297e-01 1.48540946688409e-01 + 3.23956275270876e-01 1.47933043239443e-01 + 3.39069424051884e-01 1.47069020987410e-01 + 3.54585889834479e-01 1.45943582059583e-01 + 3.70503038587840e-01 1.44545741580839e-01 + 3.86818744034228e-01 1.42880558757071e-01 + 4.03529886300044e-01 1.40949878503895e-01 + 4.20631795817686e-01 1.38743098180303e-01 + 4.38122295708788e-01 1.36280118876443e-01 + 4.55996246579842e-01 1.33558806342025e-01 + 4.74247678072064e-01 1.30579675879644e-01 + 4.92870201520873e-01 1.27343414222526e-01 + 5.11858632670824e-01 1.23865537574947e-01 + 5.31206529175901e-01 1.20155339339923e-01 + 5.50909974458698e-01 1.16240607653645e-01 + 5.70957234177731e-01 1.12113197529874e-01 + 5.91337832298221e-01 1.07776331147829e-01 + 6.12043196385659e-01 1.03247475287687e-01 + 6.33060023607835e-01 9.85266730684655e-02 + 6.54378161086711e-01 9.36324397140804e-02 + 6.75981881112925e-01 8.85633411725916e-02 + 6.97858153257143e-01 8.33339041532981e-02 + 7.19992670841439e-01 7.79576473340285e-02 + 7.42369114254639e-01 7.24430623451618e-02 + 7.64975430667051e-01 6.68198593604196e-02 + 7.87796261276916e-01 6.11074357432836e-02 + 8.10816676007818e-01 5.53301797078299e-02 + 8.34015444407408e-01 4.94904459611575e-02 + 8.57380300830358e-01 4.36292437542878e-02 + 8.80896308203363e-01 3.77798261883748e-02 + 9.04543314270347e-01 3.19572727461911e-02 + 9.28307142422559e-01 2.62037308608536e-02 + 9.52166971266270e-01 2.05309059939892e-02 + 9.76079738069090e-01 1.49147985067452e-02 + 1.00000000000000e+00 9.38745044130349e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF22_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF22_Coords.txt new file mode 100644 index 00000000..1c8c5a0a --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF22_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -8.82463593659055e-03 + 9.75234296882347e-01 -4.07195485675820e-03 + 9.50255544432051e-01 -7.98248950457765e-04 + 9.25182518319792e-01 4.59015405686792e-04 + 9.00137383192707e-01 5.03425663979333e-04 + 8.75232119805695e-01 -9.64914030717306e-04 + 8.50557709806725e-01 -3.58967102599536e-03 + 8.26180125477418e-01 -7.31987891024248e-03 + 8.02154246906259e-01 -1.20246827249572e-02 + 7.78527428533231e-01 -1.76434549167161e-02 + 7.55341868989860e-01 -2.40877649192879e-02 + 7.32587397051707e-01 -3.11356530820595e-02 + 7.10262087078449e-01 -3.86576762939743e-02 + 6.88360042084116e-01 -4.65355162763687e-02 + 6.66859377331190e-01 -5.46311434134933e-02 + 6.45731216285550e-01 -6.28088159733548e-02 + 6.24951659171662e-01 -7.09583241634137e-02 + 6.04498468332129e-01 -7.89808536353920e-02 + 5.84347224103891e-01 -8.67750304311487e-02 + 5.64484814424526e-01 -9.42686930240366e-02 + 5.44903874660855e-01 -1.01403389217168e-01 + 5.25596182786011e-01 -1.08115855460812e-01 + 5.06567529231517e-01 -1.14379226045809e-01 + 4.87823451896779e-01 -1.20164927250333e-01 + 4.69371095089600e-01 -1.25447538406269e-01 + 4.51221749635954e-01 -1.30214673126390e-01 + 4.33390892634647e-01 -1.34470878949829e-01 + 4.15893695233854e-01 -1.38223856931158e-01 + 3.98742948807582e-01 -1.41474761672022e-01 + 3.81951916654198e-01 -1.44233318989729e-01 + 3.65535794905708e-01 -1.46552646022020e-01 + 3.49504350110542e-01 -1.48404356580122e-01 + 3.33869800276634e-01 -1.49815365629171e-01 + 3.18640850767714e-01 -1.50799533979216e-01 + 3.03826511735471e-01 -1.51385076135015e-01 + 2.89432289439516e-01 -1.51597960286678e-01 + 2.75463633707156e-01 -1.51456167973636e-01 + 2.61924667579499e-01 -1.50945289406372e-01 + 2.48816759544315e-01 -1.49820290784658e-01 + 2.36142027215763e-01 -1.48337838607945e-01 + 2.23900757877441e-01 -1.46728676677109e-01 + 2.12091202442600e-01 -1.44987152492908e-01 + 2.00711798064127e-01 -1.43105988156995e-01 + 1.89759746646316e-01 -1.41083500100127e-01 + 1.79230373598411e-01 -1.38924423695571e-01 + 1.69120266929377e-01 -1.36628506888412e-01 + 1.59424268731231e-01 -1.34203523985344e-01 + 1.50133527635805e-01 -1.31586993207801e-01 + 1.41239941796693e-01 -1.28658050632062e-01 + 1.32737352696107e-01 -1.25614268186612e-01 + 1.24616514817842e-01 -1.22473225866236e-01 + 1.16865517450329e-01 -1.19256438509995e-01 + 1.09476741372708e-01 -1.15972874855589e-01 + 1.02441090309246e-01 -1.12634755981313e-01 + 9.57446861112555e-02 -1.09261541429255e-01 + 8.93769879533703e-02 -1.05864324419857e-01 + 8.33286969484173e-02 -1.02451193415354e-01 + 7.75875849096225e-02 -9.90338569650793e-02 + 7.21406034320314e-02 -9.56250005784910e-02 + 6.69801736029935e-02 -9.22271288427092e-02 + 6.20965351512147e-02 -8.88472153672261e-02 + 5.74747850597184e-02 -8.54980753096916e-02 + 5.31073683987994e-02 -8.21816673621395e-02 + 4.89861455187096e-02 -7.89006724384927e-02 + 4.51014790775358e-02 -7.56593674473605e-02 + 4.14418725835168e-02 -7.24642712815675e-02 + 3.79974745107442e-02 -6.93199929403320e-02 + 3.47604115159903e-02 -6.62284421504838e-02 + 3.17206988444021e-02 -6.31932503262627e-02 + 2.88710263785976e-02 -6.02154239665808e-02 + 2.62080930997205e-02 -5.72921577483027e-02 + 2.37188621654212e-02 -5.44305824782203e-02 + 2.14026940124619e-02 -5.16265532316101e-02 + 1.92486521358209e-02 -4.88837255462092e-02 + 1.72452841512816e-02 -4.62063853998756e-02 + 1.53928462682404e-02 -4.35906955444680e-02 + 1.36844065977878e-02 -4.10381361973572e-02 + 1.21080479082528e-02 -3.85518513625596e-02 + 1.06541599785168e-02 -3.61339264768926e-02 + 9.33426978185559e-03 -3.37752236951720e-02 + 8.13267953454782e-03 -3.14816737620833e-02 + 7.03835673364221e-03 -2.92553427534487e-02 + 6.04148662979025e-03 -2.70976270452955e-02 + 5.15689174946352e-03 -2.50014486913912e-02 + 4.36880007549257e-03 -2.29689810492558e-02 + 3.65854316758372e-03 -2.10060486233264e-02 + 2.99941013686039e-03 -1.91176201797404e-02 + 2.40980008753548e-03 -1.72965873497120e-02 + 1.93345318526703e-03 -1.55261559946178e-02 + 1.53812700170979e-03 -1.38161514056102e-02 + 1.20539343917677e-03 -1.21679475625357e-02 + 9.56760038958383e-04 -1.05800479607496e-02 + 7.65342297036178e-04 -9.05136135456472e-03 + 6.09764517824789e-04 -7.58503925452652e-03 + 4.81674424353207e-04 -6.17878150580482e-03 + 3.72236585339006e-04 -4.83104436296697e-03 + 2.71586710445666e-04 -3.54074651466179e-03 + 1.76561614166990e-04 -2.30499697365265e-03 + 8.62412519578493e-05 -1.12213213479821e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 8.47185401973777e-05 1.14027896379731e-03 + 1.71939728463488e-04 2.32205858229273e-03 + 2.61905799319850e-04 3.55614890838687e-03 + 3.56671728002566e-04 4.84438547974499e-03 + 4.56894473875460e-04 6.18967024340794e-03 + 5.71758971911553e-04 7.59303604677746e-03 + 7.12946703728524e-04 9.05548570770134e-03 + 8.90088679297868e-04 1.05800508609476e-02 + 1.11281897036842e-03 1.21649699464116e-02 + 1.40664763699671e-03 1.38109514772927e-02 + 1.76235484285765e-03 1.55183545606631e-02 + 2.19003447587729e-03 1.72891793021203e-02 + 2.70082683401069e-03 1.91181371872414e-02 + 3.29943409992815e-03 2.10099792055921e-02 + 3.93102782928047e-03 2.29804899514016e-02 + 4.63562148560807e-03 2.50203289881847e-02 + 5.43565473538957e-03 2.71263236463253e-02 + 6.33628297941001e-03 2.92962845654899e-02 + 7.33276800568200e-03 3.15359874818167e-02 + 8.41978714840133e-03 3.38503440474200e-02 + 9.61995263674526e-03 3.62317278234274e-02 + 1.09391421670310e-02 3.86808457142837e-02 + 1.23830528385306e-02 4.11976418455524e-02 + 1.39476104023128e-02 4.37869621079364e-02 + 1.56508158075923e-02 4.64407556884219e-02 + 1.75014612839761e-02 4.91580453565656e-02 + 1.95012610748503e-02 5.19411917348513e-02 + 2.16612059898247e-02 5.47854325144758e-02 + 2.39896959065856e-02 5.76882755513278e-02 + 2.64952727828800e-02 6.06474110979852e-02 + 2.91861482360375e-02 6.36603400223900e-02 + 3.20717009166476e-02 6.67228312742886e-02 + 3.51552451210013e-02 6.98359105557802e-02 + 3.84476883194282e-02 7.29939064877054e-02 + 4.19577241052818e-02 7.61935553174862e-02 + 4.56928339535472e-02 7.94323236299435e-02 + 4.96640950800607e-02 8.27032167191995e-02 + 5.38792189767346e-02 8.60023391457613e-02 + 5.83504447473849e-02 8.93201798709532e-02 + 6.30880179008144e-02 9.26492849446814e-02 + 6.81002199761747e-02 9.59845521245626e-02 + 7.33949153615851e-02 9.93210825226372e-02 + 7.89823978777915e-02 1.02650028549060e-01 + 8.48722262132926e-02 1.05962626026196e-01 + 9.10784190713352e-02 1.09240673718372e-01 + 9.76062827541888e-02 1.12481556552737e-01 + 1.04466772321452e-01 1.15670947421273e-01 + 1.11671965236896e-01 1.18789791772743e-01 + 1.19228640293147e-01 1.21830341171694e-01 + 1.27143926895481e-01 1.24781453201826e-01 + 1.35428044884835e-01 1.27624017499659e-01 + 1.44086141353379e-01 1.30349672842819e-01 + 1.53127132103188e-01 1.32937820029185e-01 + 1.62555410547095e-01 1.35241459089964e-01 + 1.72377905628829e-01 1.37295450509711e-01 + 1.82599061397815e-01 1.39200599507429e-01 + 1.93223726992680e-01 1.40941522014517e-01 + 2.04253376503725e-01 1.42520526896251e-01 + 2.15691115538017e-01 1.43922184894547e-01 + 2.27538308990768e-01 1.45144475806100e-01 + 2.39795367406813e-01 1.46188446606183e-01 + 2.52463016033809e-01 1.47052668349391e-01 + 2.65541909631568e-01 1.47734256285049e-01 + 2.79032253033613e-01 1.48196642827539e-01 + 2.92933652151481e-01 1.48484546320859e-01 + 3.07245113037153e-01 1.48208243249528e-01 + 3.21965588324161e-01 1.47617592210408e-01 + 3.37094273205868e-01 1.46767753880215e-01 + 3.52629565222472e-01 1.45662207601935e-01 + 3.68568831200908e-01 1.44292503614155e-01 + 3.84909918045890e-01 1.42653362070648e-01 + 4.01649741329745e-01 1.40746929493391e-01 + 4.18783491107945e-01 1.38561979853749e-01 + 4.36309096119333e-01 1.36119163389331e-01 + 4.54221311551285e-01 1.33415916262098e-01 + 4.72514203789032e-01 1.30453094209417e-01 + 4.91181204690089e-01 1.27230846885164e-01 + 5.10217294887795e-01 1.23765632915085e-01 + 5.29615745188874e-01 1.20065757127932e-01 + 5.49372727688106e-01 1.16159763738369e-01 + 5.69476446033723e-01 1.12039542777908e-01 + 5.89916305219489e-01 1.07708227568959e-01 + 6.10683618838738e-01 1.03183189203426e-01 + 6.31765155670346e-01 9.84652332121784e-02 + 6.53150501435068e-01 9.35722935993394e-02 + 6.74823867520210e-01 8.85032131241451e-02 + 6.96772099289498e-01 8.32725777462657e-02 + 7.18980781856151e-01 7.78940799083079e-02 + 7.41433503084832e-01 7.23764604209258e-02 + 7.64118075436013e-01 6.67495186918011e-02 + 7.87019025497992e-01 6.10329007626331e-02 + 8.10121228200712e-01 5.52509751321508e-02 + 8.33403156826935e-01 4.94056304284834e-02 + 8.56852675073043e-01 4.35391713307892e-02 + 8.80454507154744e-01 3.76843113831125e-02 + 9.04188220893009e-01 3.18558334161366e-02 + 9.28039690086919e-01 2.61061039709405e-02 + 9.51988065306611e-01 2.03482015413632e-02 + 9.75990080595429e-01 1.45876959874575e-02 + 1.00000000000000e+00 8.83858620970101e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF23_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF23_Coords.txt new file mode 100644 index 00000000..2dcebee3 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF23_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -8.21139809450505e-03 + 9.76142842133469e-01 -3.73615750355408e-03 + 9.52101373897713e-01 -6.10304280806426e-04 + 9.27972027630962e-01 7.51610694688174e-04 + 9.03861550959005e-01 9.63261392398244e-04 + 8.79868401432142e-01 -3.33217321879714e-04 + 8.56074970695499e-01 -2.53626051968576e-03 + 8.32542789395929e-01 -5.74527324899553e-03 + 8.09322839067906e-01 -9.83814732896065e-03 + 7.86458886381699e-01 -1.48643853871281e-02 + 7.63991074833837e-01 -2.06896655874153e-02 + 7.41917426367872e-01 -2.71202064324273e-02 + 7.20242581247835e-01 -3.40506239390570e-02 + 6.98961930064152e-01 -4.13612856527449e-02 + 6.78057263619977e-01 -4.89213784287057e-02 + 6.57506021858820e-01 -5.66105931522147e-02 + 6.37287503247901e-01 -6.43246573619078e-02 + 6.17383135667522e-01 -7.19732679116094e-02 + 5.97770855800075e-01 -7.94607179722445e-02 + 5.78436919352117e-01 -8.67141858187819e-02 + 5.59373209879583e-01 -9.36756409758915e-02 + 5.40570201738706e-01 -1.00281836382868e-01 + 5.22031083034862e-01 -1.06503028984052e-01 + 5.03757305858770e-01 -1.12303940051636e-01 + 4.85754185012292e-01 -1.17658749217170e-01 + 4.68029611604968e-01 -1.22549767864311e-01 + 4.50596235722804e-01 -1.26976715578814e-01 + 4.33466449688809e-01 -1.30941601459488e-01 + 4.16650268714259e-01 -1.34439253974495e-01 + 4.00159704233804e-01 -1.37483756940932e-01 + 3.84008352518328e-01 -1.40312881060739e-01 + 3.68205002950426e-01 -1.42679586968998e-01 + 3.52761641683399e-01 -1.44605028235604e-01 + 3.37686288670032e-01 -1.46093511961001e-01 + 3.22988917463881e-01 -1.47175364613660e-01 + 3.08674091631704e-01 -1.47861651710737e-01 + 2.94748692456360e-01 -1.48174065247058e-01 + 2.81216974774364e-01 -1.48100322963184e-01 + 2.68081278708605e-01 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-3.02490907877501e-02 + 8.07889819085139e-03 -2.80256331349109e-02 + 6.96708593195298e-03 -2.58576394991613e-02 + 5.94591454377916e-03 -2.37513353705315e-02 + 4.99426931002390e-03 -2.17096802022710e-02 + 4.13507451423521e-03 -1.97237639636666e-02 + 3.39667523938367e-03 -1.77802282556760e-02 + 2.75601953430367e-03 -1.58894633915468e-02 + 2.19633874865461e-03 -1.40540283526098e-02 + 1.72840307496228e-03 -1.22724114817618e-02 + 1.34286570899636e-03 -1.05443998004454e-02 + 1.01729226165425e-03 -8.87224718805503e-03 + 7.32705043016408e-04 -7.25411365114207e-03 + 5.08422707108106e-04 -5.69154437946780e-03 + 3.45530945580279e-04 -4.18459716234432e-03 + 2.00034055925006e-04 -2.72863908853638e-03 + 8.38226000491430e-05 -1.32680888135557e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 8.04217358349222e-05 1.36175324140431e-03 + 1.82860022602032e-04 2.76203880241374e-03 + 3.07707391529631e-04 4.21763686472499e-03 + 4.44549055929702e-04 5.72804069668572e-03 + 6.23812839818893e-04 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2.84877807135127e-02 5.93028159074542e-02 + 3.12521672692866e-02 6.22213658283823e-02 + 3.41995342253892e-02 6.51818699892661e-02 + 3.73378473367669e-02 6.81809116659515e-02 + 4.06757574012530e-02 7.12140270675027e-02 + 4.42154838055095e-02 7.42828638427761e-02 + 4.79678967721103e-02 7.73792453363171e-02 + 5.19403017142868e-02 8.05008840842748e-02 + 5.61387218917495e-02 8.36461359062149e-02 + 6.05744824624157e-02 8.68046432556253e-02 + 6.52533623648681e-02 8.99744768782235e-02 + 7.01859237124755e-02 9.31469184593639e-02 + 7.53814295031060e-02 9.63138316754236e-02 + 8.08473958902046e-02 9.94691758968421e-02 + 8.65903682254258e-02 1.02608950984904e-01 + 9.26191737957453e-02 1.05724688299087e-01 + 9.89427503964933e-02 1.08805284501001e-01 + 1.05572574378567e-01 1.11835726530552e-01 + 1.12512915633577e-01 1.14814012082883e-01 + 1.19773007772667e-01 1.17727286471524e-01 + 1.27363221950667e-01 1.20556889598296e-01 + 1.35289296514862e-01 1.23294787548128e-01 + 1.43556857719485e-01 1.25932505090186e-01 + 1.52174578736971e-01 1.28451369499810e-01 + 1.61146152442972e-01 1.30847460635660e-01 + 1.70478833350526e-01 1.33103875216750e-01 + 1.80176444516454e-01 1.35036359961196e-01 + 1.90244409946836e-01 1.36693107134912e-01 + 2.00686204337921e-01 1.38207445504524e-01 + 2.11505597872941e-01 1.39570306744710e-01 + 2.22703590303689e-01 1.40793968317909e-01 + 2.34282402247760e-01 1.41865906191140e-01 + 2.46243024904699e-01 1.42795952710561e-01 + 2.58585392268802e-01 1.43587041085657e-01 + 2.71309804206021e-01 1.44243663400420e-01 + 2.84416437446142e-01 1.44769416282592e-01 + 2.97905136878219e-01 1.45138883405801e-01 + 3.11775233303682e-01 1.45396185603328e-01 + 3.26025457731245e-01 1.44799633556647e-01 + 3.40654434931028e-01 1.43890189834681e-01 + 3.55661055018669e-01 1.42727607243276e-01 + 3.71043291657118e-01 1.41378512496123e-01 + 3.86798859574859e-01 1.39857189471553e-01 + 4.02924818727687e-01 1.38084176510744e-01 + 4.19418353512935e-01 1.36064257381550e-01 + 4.36274589718543e-01 1.33787632522958e-01 + 4.53491768061524e-01 1.31275824854263e-01 + 4.71064241052868e-01 1.28524300378203e-01 + 4.88986423191382e-01 1.25535254042783e-01 + 5.07252279772362e-01 1.22310892585478e-01 + 5.25856826494498e-01 1.18865894646810e-01 + 5.44792841888021e-01 1.15204498738876e-01 + 5.64056788561128e-01 1.11354270394649e-01 + 5.83637699153914e-01 1.07308615540232e-01 + 6.03526114261812e-01 1.03072921183451e-01 + 6.23713052918496e-01 9.86595204920906e-02 + 6.44187289257573e-01 9.40741686204436e-02 + 6.64938489728388e-01 8.93305116803128e-02 + 6.85952696964425e-01 8.44303114940775e-02 + 7.07217803846837e-01 7.93870888768201e-02 + 7.28720904577667e-01 7.42148757404108e-02 + 7.50447285230671e-01 6.89231193962187e-02 + 7.72384947979838e-01 6.35355666474870e-02 + 7.94520071668891e-01 5.80715917032048e-02 + 8.16839076995703e-01 5.25544618224475e-02 + 8.39322007651833e-01 4.69843270149347e-02 + 8.61958036424303e-01 4.14008883230868e-02 + 8.84732645656678e-01 3.58312967441193e-02 + 9.07627292619726e-01 3.02890268067034e-02 + 9.30629504368063e-01 2.48874125752277e-02 + 9.53718812883226e-01 1.94086902525117e-02 + 9.76855430771540e-01 1.38798239923547e-02 + 1.00000000000000e+00 8.29927788503082e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF24_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF24_Coords.txt new file mode 100644 index 00000000..a00089dc --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF24_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -7.56432337756101e-03 + 9.77604553225231e-01 -3.47082732461743e-03 + 9.55071032701306e-01 -5.30304448662040e-04 + 9.32459923743646e-01 1.00923690794973e-03 + 9.09853170336084e-01 1.50584312886866e-03 + 8.87327473250015e-01 7.33296443208864e-04 + 8.64951404122783e-01 -7.98125989400150e-04 + 8.42779347686616e-01 -3.18899672693891e-03 + 8.20856013295664e-01 -6.33165545565214e-03 + 7.99219395444539e-01 -1.04099030124611e-02 + 7.77906331230207e-01 -1.52392584340842e-02 + 7.56928024157091e-01 -2.06765813620756e-02 + 7.36299678030450e-01 -2.66551952900761e-02 + 7.16018754955252e-01 -3.30533534544358e-02 + 6.96072959120435e-01 -3.97518529143060e-02 + 6.76449892721087e-01 -4.66552132883785e-02 + 6.57133999710469e-01 -5.36687143779019e-02 + 6.38112605261403e-01 -6.07157462660716e-02 + 6.19367437057640e-01 -6.77097196723369e-02 + 6.00883733642204e-01 -7.45767507129040e-02 + 5.82652169021692e-01 -8.12594873982717e-02 + 5.64661120231064e-01 -8.76947091960666e-02 + 5.46909588628814e-01 -9.38480438378482e-02 + 5.29392452861062e-01 -9.96734252612141e-02 + 5.12112084332935e-01 -1.05144390040683e-01 + 4.95070904527429e-01 -1.10234719079896e-01 + 4.78277015297031e-01 -1.14936364522100e-01 + 4.61738338257797e-01 -1.19242177975201e-01 + 4.45460422197515e-01 -1.23136810120982e-01 + 4.29453264492553e-01 -1.26638509583062e-01 + 4.13727887480644e-01 -1.30205819336949e-01 + 3.98291508433205e-01 -1.33326242585238e-01 + 3.83155740484708e-01 -1.36012845422670e-01 + 3.68327500866002e-01 -1.38256284457854e-01 + 3.53818313097675e-01 -1.40090066630534e-01 + 3.39631224097106e-01 -1.41502568029413e-01 + 3.25775418141369e-01 -1.42521487848996e-01 + 3.12255362105731e-01 -1.43137721119343e-01 + 2.99074959326180e-01 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-9.77072151568267e-02 + 8.87200022615946e-02 -9.46941899593864e-02 + 8.31713687294055e-02 -9.16659634124004e-02 + 7.78675335828499e-02 -8.86319021093854e-02 + 7.28019558797340e-02 -8.55957945406550e-02 + 6.79637706292370e-02 -8.25702506284957e-02 + 6.33491557655127e-02 -7.95534034182216e-02 + 5.89505223815094e-02 -7.65506930086862e-02 + 5.47584337632626e-02 -7.35700421773415e-02 + 5.07700025455080e-02 -7.06090083309671e-02 + 4.69790804011980e-02 -6.76722198329940e-02 + 4.33763923900693e-02 -6.47650585882094e-02 + 3.99616877288314e-02 -6.18836100097362e-02 + 3.67243144771543e-02 -5.90366522630708e-02 + 3.36535906377128e-02 -5.62299826572433e-02 + 3.07408034874801e-02 -5.34727808644556e-02 + 2.79853608942525e-02 -5.07596977654719e-02 + 2.53827326061070e-02 -4.80869915547224e-02 + 2.29279459837821e-02 -4.54565252514460e-02 + 2.06228031205048e-02 -4.28642088454343e-02 + 1.84619544646303e-02 -4.03124511788614e-02 + 1.64345829858125e-02 -3.78029484369137e-02 + 1.45396904021833e-02 -3.53359342337824e-02 + 1.27799620292237e-02 -3.29077035519993e-02 + 1.11473325968982e-02 -3.05216692101392e-02 + 9.62594710950231e-03 -2.81847018230500e-02 + 8.20369424104832e-03 -2.58965281652211e-02 + 6.91077860021739e-03 -2.36453396059864e-02 + 5.75077692399507e-03 -2.14233053286087e-02 + 4.71542334084741e-03 -1.92417246809301e-02 + 3.79061899876188e-03 -1.71050631313951e-02 + 2.96985932957846e-03 -1.50117846448995e-02 + 2.27201302000975e-03 -1.29630892410872e-02 + 1.67294240414338e-03 -1.09597866473871e-02 + 1.13657511907321e-03 -9.00077720000924e-03 + 7.27525458994168e-04 -7.09257571552104e-03 + 4.64495970750558e-04 -5.23707262291010e-03 + 2.38906446280983e-04 -3.42683252022691e-03 + 8.17107945672561e-05 -1.67272034668398e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 7.61467549823109e-05 1.70145394345800e-03 + 2.01943167056160e-04 3.45328232459010e-03 + 3.81395185583571e-04 5.26525263642839e-03 + 5.85930307757067e-04 7.13308979231880e-03 + 8.92359097274833e-04 9.06361021019522e-03 + 1.28649070591074e-03 1.10530399913895e-02 + 1.73771156288424e-03 1.30951293142941e-02 + 2.29173728679810e-03 1.51945964609704e-02 + 2.95328678251122e-03 1.73461748802941e-02 + 3.71701635353684e-03 1.95421603635107e-02 + 4.61125731443375e-03 2.17836207464791e-02 + 5.62117485502431e-03 2.40723132909228e-02 + 6.74201573095337e-03 2.64057930966131e-02 + 7.99336891397882e-03 2.87849029776245e-02 + 9.33623835245940e-03 3.12146929013670e-02 + 1.08033908671941e-02 3.36902372052722e-02 + 1.24006058390659e-02 3.62057794756649e-02 + 1.41388224411716e-02 3.87588635013297e-02 + 1.60121791203600e-02 4.13505095288245e-02 + 1.80266176901062e-02 4.39770539483560e-02 + 2.01726496377910e-02 4.66558210289041e-02 + 2.24432591907360e-02 4.93988661013192e-02 + 2.48624128418397e-02 5.21833061903338e-02 + 2.74369393316803e-02 5.50067882169806e-02 + 3.01803236427391e-02 5.78551969434095e-02 + 3.31011277780957e-02 6.07276635672542e-02 + 3.61947490722831e-02 6.36293863780552e-02 + 3.94707009148225e-02 6.65539808380448e-02 + 4.29363788496663e-02 6.94978007459577e-02 + 4.65945188345070e-02 7.24605067989242e-02 + 5.04526910691199e-02 7.54372060067005e-02 + 5.45183753469819e-02 7.84230601340006e-02 + 5.87920295117307e-02 8.14207174473965e-02 + 6.32844638599680e-02 8.44179706830025e-02 + 6.80007504342932e-02 8.74141030770068e-02 + 7.29445664478783e-02 9.04089010923996e-02 + 7.81276359597299e-02 9.33865968836788e-02 + 8.35526287241229e-02 9.63484244894486e-02 + 8.92274088319182e-02 9.92869409674310e-02 + 9.51596585703596e-02 1.02192912158804e-01 + 1.01355662703728e-01 1.05058787711796e-01 + 1.07819844454672e-01 1.07882013438497e-01 + 1.14558671680435e-01 1.10654730370201e-01 + 1.21580083253696e-01 1.13362071814715e-01 + 1.28891465267190e-01 1.15994154001435e-01 + 1.36495420185450e-01 1.18549960475986e-01 + 1.44398412070934e-01 1.21019005454168e-01 + 1.52608066886974e-01 1.23383263452766e-01 + 1.61128449062580e-01 1.25634241263431e-01 + 1.69962766510632e-01 1.27767754750988e-01 + 1.79117204049243e-01 1.29765835285054e-01 + 1.88593114940912e-01 1.31631707748057e-01 + 1.98395080937357e-01 1.33354415033851e-01 + 2.08526007479340e-01 1.34921720796477e-01 + 2.18988897357209e-01 1.36311059161410e-01 + 2.29785665725425e-01 1.37513025729422e-01 + 2.40918346892126e-01 1.38519678887412e-01 + 2.52387177470611e-01 1.39348303006632e-01 + 2.64192954265048e-01 1.39984871282363e-01 + 2.76336067255505e-01 1.40447602438792e-01 + 2.88815683738951e-01 1.40736906171120e-01 + 3.01631419206898e-01 1.40858856604377e-01 + 3.14782681311539e-01 1.40820916427446e-01 + 3.28268735846035e-01 1.40613930928130e-01 + 3.42088471001508e-01 1.40271965125527e-01 + 3.56240175283897e-01 1.39176450123551e-01 + 3.70721945980970e-01 1.37799453202378e-01 + 3.85532182384715e-01 1.36182988362656e-01 + 4.00668176204080e-01 1.34470081033185e-01 + 4.16128201888210e-01 1.32704826044275e-01 + 4.31908053311812e-01 1.30716434338931e-01 + 4.48005347370752e-01 1.28513932612418e-01 + 4.64415106456292e-01 1.26089816273117e-01 + 4.81136073210859e-01 1.23467012252396e-01 + 4.98161952300398e-01 1.20637816866521e-01 + 5.15487718285494e-01 1.17606579649685e-01 + 5.33108194681692e-01 1.14378816873922e-01 + 5.51018453602490e-01 1.10966343454323e-01 + 5.69210481580133e-01 1.07366855818095e-01 + 5.87681208614711e-01 1.03606344948257e-01 + 6.06421001068111e-01 9.96806556147008e-02 + 6.25422226546090e-01 9.55988006622248e-02 + 6.44675430180647e-01 9.13650080051313e-02 + 6.64172612416068e-01 8.69929959888130e-02 + 6.83903569581724e-01 8.24895121586465e-02 + 7.03857290507609e-01 7.78610146655313e-02 + 7.24023353371056e-01 7.31193106689484e-02 + 7.44391280268447e-01 6.82789782351697e-02 + 7.64949089433623e-01 6.33506013277345e-02 + 7.85685088260759e-01 5.83481890301292e-02 + 8.06588113821195e-01 5.32906782138662e-02 + 8.27647073718251e-01 4.81995644109501e-02 + 8.48844538192330e-01 4.30722004585763e-02 + 8.70171786158144e-01 3.79440985437455e-02 + 8.91615519671644e-01 3.28334603720587e-02 + 9.13160235840878e-01 2.77516556132812e-02 + 9.34796121557107e-01 2.28847968463111e-02 + 9.56503322434788e-01 1.79175149301519e-02 + 9.78247647558889e-01 1.28833930947917e-02 + 1.00000000000000e+00 7.77316122569051e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF25_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF25_Coords.txt new file mode 100644 index 00000000..5fe3a0c2 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF25_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -6.90996795189652e-03 + 9.79051784906020e-01 -3.20591062468399e-03 + 9.58011274672457e-01 -4.41056971620761e-04 + 9.36903363675773e-01 1.27365925445527e-03 + 9.15785437957649e-01 2.08866878434932e-03 + 8.94712657028773e-01 1.92887691294457e-03 + 8.73739909416876e-01 1.04756555848845e-03 + 8.52914504725529e-01 -5.77456171206867e-04 + 8.32274942259497e-01 -2.85364710268578e-03 + 8.11853501515720e-01 -6.00480012734394e-03 + 7.91683745944122e-01 -9.84809619736941e-03 + 7.71789930036150e-01 -1.43020398217891e-02 + 7.52197716498017e-01 -1.93382785426476e-02 + 7.32906618429231e-01 -2.48329722311178e-02 + 7.13910194827725e-01 -3.06784131419832e-02 + 6.95206109474979e-01 -3.68037036789993e-02 + 6.76783900840165e-01 -4.31235812832689e-02 + 6.58636732971251e-01 -4.95749936250298e-02 + 6.40750087000464e-01 -5.60803786556861e-02 + 6.23108194383111e-01 -6.25648008542080e-02 + 6.05700531557994e-01 -6.89715799959822e-02 + 5.88513399014437e-01 -7.52375218141829e-02 + 5.71541652837112e-01 -8.13236706836220e-02 + 5.54773663342737e-01 -8.71732800644328e-02 + 5.38208887696389e-01 -9.27592498440937e-02 + 5.21844331935521e-01 -9.80469149474190e-02 + 5.05683594732971e-01 -1.03020537017842e-01 + 4.89730171283752e-01 -1.07663900884601e-01 + 4.73985188195639e-01 -1.11951580262165e-01 + 4.58456648737569e-01 -1.15899775851639e-01 + 4.43153026810978e-01 -1.20020177950560e-01 + 4.28079983149119e-01 -1.23724613060294e-01 + 4.13248761562680e-01 -1.27020701972646e-01 + 3.98665187483912e-01 -1.29889315015525e-01 + 3.84342319046781e-01 -1.32366636853445e-01 + 3.70281701542905e-01 -1.34421368547331e-01 + 3.56494799430581e-01 -1.36087238593843e-01 + 3.42986289523419e-01 -1.37357755402807e-01 + 3.29761622885635e-01 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-4.03776427481770e-02 + 1.74344580911675e-02 -3.77466674771731e-02 + 1.52861705937629e-02 -3.51447522958208e-02 + 1.32695260256556e-02 -3.25794065533110e-02 + 1.13813272654342e-02 -3.00471563676276e-02 + 9.65898712950190e-03 -2.75333232210894e-02 + 8.08155935902643e-03 -2.50355491241652e-02 + 6.65541769422626e-03 -2.25660334545810e-02 + 5.36910663494096e-03 -2.01311292826235e-02 + 4.19901797256922e-03 -1.77292764366712e-02 + 3.19195638788689e-03 -1.53630739376981e-02 + 2.32209781048333e-03 -1.30319016666417e-02 + 1.53644454079846e-03 -1.07353929558163e-02 + 9.44457823853916e-04 -8.48498302048932e-03 + 5.82282552724702e-04 -6.28437677557031e-03 + 2.79797716122703e-04 -4.12336408929500e-03 + 8.01825423805274e-05 -2.02045958246308e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 7.27481971794514e-05 2.03253534122420e-03 + 2.24119822441770e-04 4.13242423123724e-03 + 4.54353043427967e-04 6.29723664202138e-03 + 7.25911065833949e-04 8.51896646047437e-03 + 1.15824519045566e-03 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5.03448265559965e-02 7.37280629139574e-02 + 5.45048490210109e-02 7.66969024895348e-02 + 5.88667212624090e-02 7.96617886230915e-02 + 6.34376218430832e-02 8.26163666818840e-02 + 6.82238711518841e-02 8.55554276954450e-02 + 7.32241829389096e-02 8.84826106361476e-02 + 7.84493081684038e-02 9.13817175580576e-02 + 8.39021076356463e-02 9.42535868383690e-02 + 8.95839357467278e-02 9.70994214118358e-02 + 9.55069115103113e-02 9.98980967272800e-02 + 1.01670626295308e-01 1.02653978781261e-01 + 1.08080272896129e-01 1.05360887370290e-01 + 1.14741968547590e-01 1.08008501375277e-01 + 1.21660778822698e-01 1.10587775677240e-01 + 1.28839025836469e-01 1.13097587715781e-01 + 1.36280841388445e-01 1.15530682154723e-01 + 1.43993175323776e-01 1.17868466227087e-01 + 1.51979363994295e-01 1.20106134642064e-01 + 1.60240358954647e-01 1.22243647030130e-01 + 1.68779882153193e-01 1.24272863043493e-01 + 1.77602841555064e-01 1.26176385527535e-01 + 1.86711644252493e-01 1.27945266530296e-01 + 1.96107103772600e-01 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4.92276868993485e-01 1.18462998717239e-01 + 5.08506539530098e-01 1.15730297851643e-01 + 5.24991239165174e-01 1.12824200948091e-01 + 5.41726496973228e-01 1.09751190784078e-01 + 5.58707986188693e-01 1.06520060382622e-01 + 5.75930834781045e-01 1.03139789300860e-01 + 5.93386245129911e-01 9.96015966856668e-02 + 6.11071609997387e-01 9.59299145672758e-02 + 6.28978616255575e-01 9.21230024006773e-02 + 6.47101440422570e-01 8.81934629508471e-02 + 6.65430158423062e-01 8.41374991675851e-02 + 6.83959965052850e-01 7.99767137056431e-02 + 7.02680785234760e-01 7.57110238797591e-02 + 7.21584524810879e-01 7.13515376484831e-02 + 7.40662430560521e-01 6.69083654908165e-02 + 7.59906428424182e-01 6.23966262173392e-02 + 7.79307241731570e-01 5.78280291843169e-02 + 7.98853480073595e-01 5.32069422153383e-02 + 8.18536612417361e-01 4.85518691766150e-02 + 8.38348008636851e-01 4.38825514234465e-02 + 8.58272740493840e-01 3.91935723287226e-02 + 8.78304172167859e-01 3.45162967179692e-02 + 8.98430213345024e-01 2.98600656550237e-02 + 9.18638370858659e-01 2.52341648010477e-02 + 9.38921465088871e-01 2.08418931868186e-02 + 9.59260249204513e-01 1.63700067511036e-02 + 9.79626073331625e-01 1.18455832014158e-02 + 1.00000000000000e+00 7.26000008758432e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF26_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF26_Coords.txt new file mode 100644 index 00000000..78a9a797 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF26_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -6.27548680628733e-03 + 9.79897896066398e-01 -2.88100938002223e-03 + 9.59730261051089e-01 -2.48646511733163e-04 + 9.39501181403885e-01 1.58812893692097e-03 + 9.19253685583499e-01 2.66331305516477e-03 + 8.99030339193690e-01 2.91993880314394e-03 + 8.78878031053569e-01 2.38861122935718e-03 + 8.58839934355517e-01 1.12181574398836e-03 + 8.38950917754029e-01 -7.98395603403523e-04 + 8.19239919523370e-01 -3.43083945751242e-03 + 7.99738589204766e-01 -6.69764467727776e-03 + 7.80478811433425e-01 -1.05766643177347e-02 + 7.61492363619193e-01 -1.50619517357643e-02 + 7.42779957957341e-01 -2.00284429351637e-02 + 7.24338576407926e-01 -2.53751507348420e-02 + 7.06171765169634e-01 -3.10455496457105e-02 + 6.88272041175159e-01 -3.69599064340915e-02 + 6.70635982119011e-01 -4.30630950931861e-02 + 6.53251263553763e-01 -4.92828312654591e-02 + 6.36101528149825e-01 -5.55435645995022e-02 + 6.19175552198615e-01 -6.17890076120828e-02 + 6.02458422155477e-01 -6.79559813922944e-02 + 5.85942570607525e-01 -7.40028506960966e-02 + 5.69612562834441e-01 -7.98666247372443e-02 + 5.53466152216717e-01 -8.55198311697876e-02 + 5.37497178699624e-01 -9.09228670519637e-02 + 5.21706608211975e-01 -9.60554978447310e-02 + 5.06095348080997e-01 -1.00896207565631e-01 + 4.90661939526162e-01 -1.05413678519611e-01 + 4.75413219979189e-01 -1.09610411484604e-01 + 4.60356173420848e-01 -1.13694012376059e-01 + 4.45495550568165e-01 -1.17411208543187e-01 + 4.30842379309956e-01 -1.20771627637541e-01 + 4.16401846768110e-01 -1.23757972990762e-01 + 4.02187908274686e-01 -1.26407040099974e-01 + 3.88201231209126e-01 -1.28681678660864e-01 + 3.74454613117445e-01 -1.30619307476714e-01 + 3.60952853551843e-01 -1.32213884198423e-01 + 3.47702308442112e-01 -1.33453605072464e-01 + 3.34710687570464e-01 -1.34377861550423e-01 + 3.21982407843259e-01 -1.35006179747371e-01 + 3.09522641967504e-01 -1.35343548930300e-01 + 2.97335142729240e-01 -1.35407149219830e-01 + 2.85423745712349e-01 -1.35209058962805e-01 + 2.73791096325235e-01 -1.34751908560863e-01 + 2.62439577166538e-01 -1.34049738653879e-01 + 2.51370313684989e-01 -1.33128582719707e-01 + 2.40585254570385e-01 -1.32039364891975e-01 + 2.30084050717160e-01 -1.30921128291335e-01 + 2.19868349503182e-01 -1.29616971692603e-01 + 2.09935590681986e-01 -1.28154872746361e-01 + 2.00287214803938e-01 -1.26527105312497e-01 + 1.90921515401614e-01 -1.24749352797282e-01 + 1.81836784290526e-01 -1.22830838469943e-01 + 1.73032114692883e-01 -1.20779026277013e-01 + 1.64504490414414e-01 -1.18604601911880e-01 + 1.56249446471325e-01 -1.16324860910107e-01 + 1.48264127853011e-01 -1.13946958715928e-01 + 1.40545038630696e-01 -1.11479659023348e-01 + 1.33091004443564e-01 -1.08924314328813e-01 + 1.25894233808957e-01 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The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -5.67403868393575e-03 + 9.79741045648661e-01 -2.42701798235721e-03 + 9.59418734206259e-01 1.45817993657089e-04 + 9.39037829344021e-01 2.03706000542212e-03 + 9.18639734339343e-01 3.24008089685812e-03 + 8.98267369292816e-01 3.56427248375033e-03 + 8.77968065224077e-01 2.97603215185010e-03 + 8.57785318219346e-01 1.55947448530291e-03 + 8.37754485568274e-01 -6.00230130933099e-04 + 8.17905732957675e-01 -3.27975099021012e-03 + 7.98271459674006e-01 -6.56643738824756e-03 + 7.78883955077259e-01 -1.04697918471843e-02 + 7.59774145953394e-01 -1.49777372785481e-02 + 7.40943035262346e-01 -1.99657343796035e-02 + 7.22388114137865e-01 -2.53335240994536e-02 + 7.04112564289356e-01 -3.10222695240268e-02 + 6.86108664224081e-01 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2.80103871369643e-02 + 9.21186490028025e-01 2.36412035750401e-02 + 9.40840463067174e-01 1.92394132556927e-02 + 9.60542395626828e-01 1.48796822371786e-02 + 9.80266637238719e-01 1.05503885298509e-02 + 1.00000000000000e+00 6.26505689076515e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF28_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF28_Coords.txt new file mode 100644 index 00000000..962a29a9 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF28_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -5.07931290625881e-03 + 9.78759069862791e-01 -1.77417080855189e-03 + 9.57455046919601e-01 8.34169870768012e-04 + 9.36102882730402e-01 2.73403129635382e-03 + 9.14741823948585e-01 3.92622470916057e-03 + 8.93420713684284e-01 4.15751919324668e-03 + 8.72191598049569e-01 3.39510168565109e-03 + 8.51100824918164e-01 1.77627582614882e-03 + 8.30187155639255e-01 -5.91463369305793e-04 + 8.09487302975761e-01 -3.50871316730807e-03 + 7.89037621347337e-01 -7.08256909391424e-03 + 7.68869531320921e-01 -1.12921021087019e-02 + 7.49008105125871e-01 -1.60905525290312e-02 + 7.29455206468978e-01 -2.13561089072927e-02 + 7.10209375002886e-01 -2.69893785892337e-02 + 6.91270152642739e-01 -3.29163938148530e-02 + 6.72627738437084e-01 -3.90478971868268e-02 + 6.54273968889022e-01 -4.53123396424792e-02 + 6.36196054110899e-01 -5.16335778873107e-02 + 6.18378049587102e-01 -5.79335747384585e-02 + 6.00808792498313e-01 -6.41518117077036e-02 + 5.83476081464459e-01 -7.02276446974945e-02 + 5.66373199940814e-01 -7.61159641162185e-02 + 5.49490310736459e-01 -8.17645969889591e-02 + 5.32825893883027e-01 -8.71416229623088e-02 + 5.16377030041224e-01 -9.22111122323383e-02 + 5.00147156065027e-01 -9.69551749282225e-02 + 4.84141136479792e-01 -1.01363266667174e-01 + 4.68361088407377e-01 -1.05413068836821e-01 + 4.52815527134986e-01 -1.09098795345862e-01 + 4.37512627544965e-01 -1.12191020625428e-01 + 4.22458061184345e-01 -1.14933239854340e-01 + 4.07662362525996e-01 -1.17354698455944e-01 + 3.93131276265282e-01 -1.19466460413223e-01 + 3.78876371904763e-01 -1.21304651773868e-01 + 3.64898988423553e-01 -1.22858767998435e-01 + 3.51209126238965e-01 -1.24169232637766e-01 + 3.37810595758489e-01 -1.25228137448965e-01 + 3.24707600617416e-01 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4.88636103070399e-02 7.04569390976742e-02 + 5.29276937714780e-02 7.32993463636303e-02 + 5.71881886728240e-02 7.61394613516280e-02 + 6.16521473909945e-02 7.89714507996290e-02 + 6.63264854493882e-02 8.17892149673703e-02 + 7.12108863597540e-02 8.45960293898340e-02 + 7.63154573583305e-02 8.73767529793241e-02 + 8.16434438696692e-02 9.01308330936490e-02 + 8.71967809712278e-02 9.28593083249690e-02 + 9.29861960270380e-02 9.55443806340739e-02 + 9.90114209148622e-02 9.81912772602473e-02 + 1.05277926361640e-01 1.00793364629599e-01 + 1.11791811246647e-01 1.03341288703187e-01 + 1.18558501469732e-01 1.05826535574825e-01 + 1.25581028029529e-01 1.08247670257292e-01 + 1.32863587756823e-01 1.10598829710272e-01 + 1.40413212085224e-01 1.12861710911733e-01 + 1.48233123450538e-01 1.15032309205900e-01 + 1.56325743459978e-01 1.17109472745647e-01 + 1.64694842248188e-01 1.19087844630684e-01 + 1.73344985305097e-01 1.20952712609130e-01 + 1.82279618595638e-01 1.22696372128947e-01 + 1.91500849370652e-01 1.24315190343453e-01 + 2.01012965207770e-01 1.25790803762581e-01 + 2.10816302410663e-01 1.27133313064226e-01 + 2.20913009206459e-01 1.28346987928072e-01 + 2.31306251606215e-01 1.29124600786585e-01 + 2.41997686108533e-01 1.29598156235129e-01 + 2.52988823179835e-01 1.29985931099543e-01 + 2.64280929945187e-01 1.30271096138049e-01 + 2.75874735130741e-01 1.30462561970147e-01 + 2.87770395562822e-01 1.30535587133523e-01 + 2.99968889986730e-01 1.30506634928112e-01 + 3.12469889713620e-01 1.30354427298291e-01 + 3.25273136309465e-01 1.30070865514745e-01 + 3.38378058156743e-01 1.29644763748054e-01 + 3.51784071831834e-01 1.29063947113764e-01 + 3.65489935520628e-01 1.28327206562353e-01 + 3.79494016904881e-01 1.27427265103237e-01 + 3.93794142700315e-01 1.26321390828251e-01 + 4.08388494677736e-01 1.25020699923467e-01 + 4.23273751214338e-01 1.23428705690998e-01 + 4.38449023184147e-01 1.21564127458960e-01 + 4.53909044617285e-01 1.19499544771642e-01 + 4.69652211025295e-01 1.17250327008969e-01 + 4.85673624880008e-01 1.14811164473538e-01 + 5.01971831021026e-01 1.12200339745912e-01 + 5.18540465681811e-01 1.09410804226609e-01 + 5.35375239805050e-01 1.06449897469931e-01 + 5.52471137015526e-01 1.03322427011034e-01 + 5.69823882155297e-01 1.00041459177470e-01 + 5.87424536390005e-01 9.65980052747351e-02 + 6.05269320712368e-01 9.30114164215713e-02 + 6.23350003912149e-01 8.92815368342969e-02 + 6.41660705707632e-01 8.54223873509465e-02 + 6.60191372818727e-01 8.14312694173232e-02 + 6.78936344189552e-01 7.73275864063319e-02 + 6.97886487865566e-01 7.31182055568951e-02 + 7.17033605603755e-01 6.88158410133258e-02 + 7.36369388572263e-01 6.44353354758884e-02 + 7.55884801812479e-01 5.99901583767167e-02 + 7.75569933118936e-01 5.54922143471618e-02 + 7.95414150366974e-01 5.09530568377930e-02 + 8.15407242505679e-01 4.63875310776136e-02 + 8.35539349320223e-01 4.18142087255355e-02 + 8.55796356354238e-01 3.72353983554263e-02 + 8.76168145132350e-01 3.26721170829936e-02 + 8.96640975774816e-01 2.81315065848594e-02 + 9.17202078061274e-01 2.36267809132743e-02 + 9.37840508339705e-01 1.91047786600906e-02 + 9.58536232986692e-01 1.46286434758752e-02 + 9.79261424141970e-01 1.01852490851282e-02 + 1.00000000000000e+00 5.78986975720379e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF29_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF29_Coords.txt new file mode 100644 index 00000000..fb693256 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF29_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -4.49625939740452e-03 + 9.77457853208364e-01 -1.04316597600737e-03 + 9.54852963815056e-01 1.63555784437397e-03 + 9.32213783357029e-01 3.50730746196549e-03 + 9.09576700744022e-01 4.60757296789467e-03 + 8.86998407669373e-01 4.68081430367886e-03 + 8.64537198216728e-01 3.72271423521479e-03 + 8.42243199165007e-01 1.92239950430055e-03 + 8.20159682584557e-01 -5.96865324129041e-04 + 7.98332036772446e-01 -3.81219520162389e-03 + 7.76801857097513e-01 -7.76657962862105e-03 + 7.55599412888537e-01 -1.23818300163157e-02 + 7.34742018498701e-01 -1.75652287574438e-02 + 7.14232678210926e-01 -2.31985790867254e-02 + 6.94071321070827e-01 -2.91836364125778e-02 + 6.74252665900160e-01 -3.54263830827288e-02 + 6.54764156255591e-01 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2.82919179045392e-02 + 9.11922331570745e-01 2.36075853088273e-02 + 9.33865266678883e-01 1.90061749563297e-02 + 9.55877865767872e-01 1.44253696213052e-02 + 9.77929415714106e-01 9.86017810574581e-03 + 1.00000000000000e+00 5.32180221795630e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF30_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF30_Coords.txt new file mode 100644 index 00000000..9aa2065c --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF30_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.93323218112574e-03 + 9.76323470833739e-01 -3.61167224034221e-04 + 9.52584504368996e-01 2.36200917930035e-03 + 9.28823321232748e-01 4.17718024662597e-03 + 9.05073818994016e-01 5.16415808743744e-03 + 8.81399531630570e-01 5.09096174883476e-03 + 8.57864200119782e-01 3.98265418559522e-03 + 8.34521245636961e-01 2.05039829123919e-03 + 8.11417872635709e-01 -5.97848046449028e-04 + 7.88607032621726e-01 -4.07692785365896e-03 + 7.66134889949618e-01 -8.36305167425931e-03 + 7.44030710314936e-01 -1.33320007602753e-02 + 7.22305044863544e-01 -1.88509920322628e-02 + 7.00961892216592e-01 -2.48049799541478e-02 + 6.80002392672937e-01 -3.10967207992328e-02 + 6.59417060349373e-01 -3.76147177012136e-02 + 6.39190936603501e-01 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1.10041494000889e-01 + 1.57362637707264e-01 1.12173428790639e-01 + 1.66182348083024e-01 1.14207532128983e-01 + 1.75343733407111e-01 1.16150220401422e-01 + 1.84853479218650e-01 1.17886445994320e-01 + 1.94718419971344e-01 1.19452624369295e-01 + 2.04944335609019e-01 1.20904257975971e-01 + 2.15536605613641e-01 1.22223960879677e-01 + 2.26499442106346e-01 1.23402886400648e-01 + 2.37836353342475e-01 1.24429064080778e-01 + 2.49551468557503e-01 1.25301722141646e-01 + 2.61647978108495e-01 1.26002114425625e-01 + 2.74128110585591e-01 1.26519005923695e-01 + 2.86993844874052e-01 1.26831148273081e-01 + 3.00246791085851e-01 1.26914393880050e-01 + 3.13886888509904e-01 1.26775293883833e-01 + 3.27914108157883e-01 1.26409149584926e-01 + 3.42327450722950e-01 1.25746584815274e-01 + 3.57126259548593e-01 1.24816468402290e-01 + 3.72308198427630e-01 1.23678019753342e-01 + 3.87872242208834e-01 1.22408465645943e-01 + 4.03815113655421e-01 1.20892501138629e-01 + 4.20135370451198e-01 1.19144468961662e-01 + 4.36828614108603e-01 1.17156007567097e-01 + 4.53891352664245e-01 1.14931437545369e-01 + 4.71319197288225e-01 1.12475372744814e-01 + 4.89107519683607e-01 1.09794165055402e-01 + 5.07248827524868e-01 1.06880395012909e-01 + 5.25739980248093e-01 1.03758998064230e-01 + 5.44572753024734e-01 1.00428819922214e-01 + 5.63740409976877e-01 9.69009341299154e-02 + 5.83233202597139e-01 9.31753092256823e-02 + 6.03042830684245e-01 8.92642559809137e-02 + 6.23159577875907e-01 8.51775215305777e-02 + 6.43571983464834e-01 8.09200190459371e-02 + 6.64272656875951e-01 7.65213597320201e-02 + 6.85249472323694e-01 7.19915770223985e-02 + 7.06492892337749e-01 6.73572355799172e-02 + 7.27988877474063e-01 6.26277837466349e-02 + 7.49722784428381e-01 5.78140865027228e-02 + 7.71685127823939e-01 5.29544996367203e-02 + 7.93858948778344e-01 4.80570291694600e-02 + 8.16228764331545e-01 4.31401192179182e-02 + 8.38778916193787e-01 3.82252136892333e-02 + 8.61489593052035e-01 3.33177109081651e-02 + 8.84342183716357e-01 2.84316009527550e-02 + 9.07319522852483e-01 2.35906895671876e-02 + 9.30399706920200e-01 1.88998238809764e-02 + 9.53560338622756e-01 1.42114480062832e-02 + 9.76768189504558e-01 9.52625743455217e-03 + 1.00000000000000e+00 4.85271819555733e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF31_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF31_Coords.txt new file mode 100644 index 00000000..ad67eb60 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF31_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.39909427730294e-03 + 9.75739786245093e-01 1.66667066115984e-04 + 9.51417292282270e-01 2.85912858145949e-03 + 9.27078794400706e-01 4.60341829559475e-03 + 9.02756908276111e-01 5.50613391539154e-03 + 8.78518688512159e-01 5.35971397021267e-03 + 8.54430678728430e-01 4.19771208973180e-03 + 8.30547995197446e-01 2.20301177833617e-03 + 8.06919865739493e-01 -5.79858711530448e-04 + 7.83603133430182e-01 -4.21344714779629e-03 + 7.60646313547970e-01 -8.67026400438177e-03 + 7.38078155379423e-01 -1.38212050569975e-02 + 7.15905730132804e-01 -1.95128719564531e-02 + 6.94133548055599e-01 -2.56318405987101e-02 + 6.72763372684357e-01 -3.20813822416317e-02 + 6.51783554648899e-01 -3.87410062721133e-02 + 6.31177899280420e-01 -4.54965105369282e-02 + 6.10925694660405e-01 -5.22336503936310e-02 + 5.91012551287536e-01 -5.88655748559732e-02 + 5.71423674899189e-01 -6.53081406311836e-02 + 5.52148193637985e-01 -7.14901559459290e-02 + 5.33180938251479e-01 -7.73573215393409e-02 + 5.14517802334726e-01 -8.28563570797554e-02 + 4.96163719036651e-01 -8.79634154002229e-02 + 4.78119325106735e-01 -9.26355107282512e-02 + 4.60390443057936e-01 -9.68468884471846e-02 + 4.42987218340636e-01 -1.00586419659736e-01 + 4.25924937239420e-01 -1.03872084322774e-01 + 4.09215183274954e-01 -1.06705265246540e-01 + 3.92870904133390e-01 -1.09114012391344e-01 + 3.76903551727443e-01 -1.11249616161404e-01 + 3.61321283604413e-01 -1.12961375193398e-01 + 3.46133441293176e-01 -1.14278538699435e-01 + 3.31347292055281e-01 -1.15229726056944e-01 + 3.16968253164255e-01 -1.15836939720711e-01 + 3.02999519108095e-01 -1.16118986482656e-01 + 2.89443821855832e-01 -1.16121220594512e-01 + 2.76302470447169e-01 -1.15822471042447e-01 + 2.63574099608091e-01 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-2.43882221823268e-02 + 9.09815040788543e-03 -2.26529512593523e-02 + 7.84170242489815e-03 -2.09448097537099e-02 + 6.68403239544467e-03 -1.92756021526446e-02 + 5.54949184750671e-03 -1.76976772112062e-02 + 4.52160737553635e-03 -1.61446314317938e-02 + 3.64340860979854e-03 -1.45962578918390e-02 + 2.91062290643606e-03 -1.30587774980858e-02 + 2.29855508780695e-03 -1.15476776744096e-02 + 1.81812065527304e-03 -1.00675799462668e-02 + 1.44375175176043e-03 -8.62806010495813e-03 + 1.16809719336443e-03 -7.23388244617354e-03 + 9.32608159232356e-04 -5.89314179331030e-03 + 7.20674256176374e-04 -4.60933828270470e-03 + 5.25688647449223e-04 -3.37988707954523e-03 + 3.40835589883743e-04 -2.20290202941760e-03 + 1.64346865984056e-04 -1.07689387957650e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 1.53869139937573e-04 1.07807588078786e-03 + 3.04071965837616e-04 2.20647324921419e-03 + 4.54457975871383e-04 3.38656052640254e-03 + 6.05078767614746e-04 4.61959410165525e-03 + 7.61247128100513e-04 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2.79759859059517e-02 4.92352578533138e-02 + 3.07029304318938e-02 5.16235456328616e-02 + 3.35978371577263e-02 5.40497764925380e-02 + 3.66680611492222e-02 5.65113655174356e-02 + 3.99238398646998e-02 5.90023806866969e-02 + 4.33700405749277e-02 6.15230992074648e-02 + 4.70152521726131e-02 6.40681891966492e-02 + 5.08671764876895e-02 6.66341185196324e-02 + 5.49328721816193e-02 6.92189285992367e-02 + 5.92189576390632e-02 7.18213097075055e-02 + 6.37303796474003e-02 7.44425317192721e-02 + 6.84775248970213e-02 7.70741944675256e-02 + 7.34689186697189e-02 7.97116805421378e-02 + 7.87128152239401e-02 8.23507271150428e-02 + 8.42173399946330e-02 8.49871998752260e-02 + 8.99905430235632e-02 8.76169020885232e-02 + 9.60412224669393e-02 9.02320979314852e-02 + 1.02378713005334e-01 9.28247078569560e-02 + 1.09011725666261e-01 9.53883054988788e-02 + 1.15948483072861e-01 9.79176716209780e-02 + 1.23196986782368e-01 1.00406512606601e-01 + 1.30765902539138e-01 1.02847233856467e-01 + 1.38664359933785e-01 1.05226821035496e-01 + 1.46901957132397e-01 1.07529696890148e-01 + 1.55485944052396e-01 1.09749789749515e-01 + 1.64423182165898e-01 1.11884391967652e-01 + 1.73721200457221e-01 1.13911272563702e-01 + 1.83388074262724e-01 1.15821004647700e-01 + 1.93430606694714e-01 1.17604750981877e-01 + 2.03855162750145e-01 1.19246902631310e-01 + 2.14666789336154e-01 1.20736420536841e-01 + 2.25869797868798e-01 1.22066280667620e-01 + 2.37469072589833e-01 1.23223955194771e-01 + 2.49468647185969e-01 1.24193911237087e-01 + 2.61871346255825e-01 1.24968075308936e-01 + 2.74679759905621e-01 1.25525906006853e-01 + 2.87896023922084e-01 1.25844883871652e-01 + 3.01520360642209e-01 1.25929884597590e-01 + 3.15553125311262e-01 1.25789254513640e-01 + 3.29993599962861e-01 1.25351297741305e-01 + 3.44841406308180e-01 1.24662975309263e-01 + 3.60094444292175e-01 1.23737418968654e-01 + 3.75751656165542e-01 1.22610460751335e-01 + 3.91810241285897e-01 1.21225971077480e-01 + 4.08268796201183e-01 1.19598046643594e-01 + 4.25123042017541e-01 1.17717594534165e-01 + 4.42368998657365e-01 1.15585589387212e-01 + 4.60002750578870e-01 1.13209439924516e-01 + 4.78019588187282e-01 1.10595261345016e-01 + 4.96411425802417e-01 1.07732704017816e-01 + 5.15175394762687e-01 1.04649547791519e-01 + 5.34303441349070e-01 1.01346515873086e-01 + 5.53788121077760e-01 9.78326981073893e-02 + 5.73619321825297e-01 9.41080928262103e-02 + 5.93788163463361e-01 9.01846009881958e-02 + 6.14285010371086e-01 8.60749523033904e-02 + 6.35097011970718e-01 8.17805874062051e-02 + 6.56217195003967e-01 7.73365680304052e-02 + 6.77632492460534e-01 7.27522851846285e-02 + 6.99333072430285e-01 6.80571126677167e-02 + 7.21303696158036e-01 6.32595351785844e-02 + 7.43528586544760e-01 5.83701685478656e-02 + 7.65998533028662e-01 5.34337916704591e-02 + 7.88694959628150e-01 4.84567715698254e-02 + 8.11601035907789e-01 4.34575217978679e-02 + 8.34700733602412e-01 3.84620719915582e-02 + 8.57971918537177e-01 3.34720774754900e-02 + 8.81394812126103e-01 2.85031695282134e-02 + 9.04951195757996e-01 2.35816921636677e-02 + 9.28616539385671e-01 1.87519658334635e-02 + 9.52367879264581e-01 1.39421026241459e-02 + 9.76170692701358e-01 9.14702646089212e-03 + 1.00000000000000e+00 4.37932834150154e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF32_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF32_Coords.txt new file mode 100644 index 00000000..6c3481b8 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF32_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -2.86933612157191e-03 + 9.75710581955689e-01 5.51477867577173e-04 + 9.51359031596632e-01 3.13262961853299e-03 + 9.26991894625622e-01 4.80111337820540e-03 + 9.02641669985214e-01 5.66121921621952e-03 + 8.78375551244010e-01 5.52137617785977e-03 + 8.54260189031929e-01 4.39735522731236e-03 + 8.30350764819393e-01 2.40219875532723e-03 + 8.06696583075141e-01 -5.00952188830051e-04 + 7.83354642102012e-01 -4.16213194475111e-03 + 7.60373540303087e-01 -8.61161677423921e-03 + 7.37781971622506e-01 -1.37504882375816e-02 + 7.15586869697147e-01 -1.94259517535702e-02 + 6.93792798799077e-01 -2.55260896373486e-02 + 6.72401581934057e-01 -3.19552843103034e-02 + 6.51401499009391e-01 -3.85932302535030e-02 + 6.30776330468193e-01 -4.53260559798622e-02 + 6.10505284953472e-01 -5.20396662533520e-02 + 5.90573982420126e-01 -5.86474213601350e-02 + 5.70967654303317e-01 -6.50651701311649e-02 + 5.51675431418049e-01 -7.12212133883194e-02 + 5.32692225296455e-01 -7.70617165566036e-02 + 5.14013964216947e-01 -8.25336151006485e-02 + 4.95645713543472e-01 -8.76132426767312e-02 + 4.77588104389030e-01 -9.22563408198895e-02 + 4.59847027738872e-01 -9.64367147020175e-02 + 4.42432692902487e-01 -1.00143384153325e-01 + 4.25360472301764e-01 -1.03394173973710e-01 + 4.08642045684131e-01 -1.06191287249211e-01 + 3.92290400221153e-01 -1.08544986908926e-01 + 3.76317022031866e-01 -1.10139175084822e-01 + 3.60730092418504e-01 -1.11371512532470e-01 + 3.45538931592235e-01 -1.12261191009945e-01 + 3.30750821422830e-01 -1.12835269970873e-01 + 3.16371112086567e-01 -1.13103574620437e-01 + 3.02403014504912e-01 -1.13082757921765e-01 + 2.88849183529447e-01 -1.12821581450485e-01 + 2.75710898902246e-01 -1.12286327404734e-01 + 2.62986738758329e-01 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-2.35183857078230e-02 + 9.02513409957092e-03 -2.18880487579211e-02 + 7.77661519691035e-03 -2.02767632089874e-02 + 6.62655361045153e-03 -1.87005437179072e-02 + 5.49884834104592e-03 -1.72060551400348e-02 + 4.47717226558900e-03 -1.57381095971917e-02 + 3.60515260195545e-03 -1.42655774200156e-02 + 2.87842186472125e-03 -1.27912524665274e-02 + 2.27218694288842e-03 -1.13335943630618e-02 + 1.79771419844169e-03 -9.89508410920731e-03 + 1.42883574258884e-03 -8.48720722363950e-03 + 1.15831794062774e-03 -7.11636221746300e-03 + 9.30636249531746e-04 -5.79723280350945e-03 + 7.23870989558607e-04 -4.53364765449117e-03 + 5.30112500189225e-04 -3.32376787121142e-03 + 3.52782657913539e-04 -2.16590639702834e-03 + 1.80335397902936e-04 -1.05857850063155e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 1.69715796269172e-04 1.06014319106919e-03 + 3.21704227944512e-04 2.17080604943226e-03 + 4.60023854570542e-04 3.33301245462774e-03 + 6.10259476100310e-04 4.54803964186977e-03 + 7.63254914856163e-04 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2.77812429214905e-02 4.77512403299201e-02 + 3.04953176572188e-02 5.00605553063858e-02 + 3.33770560169661e-02 5.24080586925027e-02 + 3.64338172837324e-02 5.47908985454538e-02 + 3.96758623516985e-02 5.72045278709751e-02 + 4.31081148620460e-02 5.96487864870898e-02 + 4.67391469620273e-02 6.21190717516457e-02 + 5.05766912034182e-02 6.46141156063287e-02 + 5.46278596855443e-02 6.71316672087533e-02 + 5.88992343795577e-02 6.96702967966609e-02 + 6.33958210810660e-02 7.22303205575746e-02 + 6.81280497888368e-02 7.48043751863431e-02 + 7.31044690486392e-02 7.73883294092361e-02 + 7.83333610762029e-02 7.99783703744675e-02 + 8.38229021165262e-02 8.25705985893102e-02 + 8.95811846390999e-02 8.51601173812468e-02 + 9.56170142055573e-02 8.77423595089163e-02 + 1.01939781818762e-01 9.03107543450649e-02 + 1.08558265316547e-01 9.28580826494489e-02 + 1.15480744127304e-01 9.53765928581059e-02 + 1.22715247925958e-01 9.78621377686747e-02 + 1.30270506312440e-01 1.00304043054231e-01 + 1.38155703711192e-01 1.02694528398231e-01 + 1.46380476666041e-01 1.05026259286590e-01 + 1.54952155330125e-01 1.07293322081246e-01 + 1.63877705055846e-01 1.09470413188966e-01 + 1.73164612629031e-01 1.11566635995441e-01 + 1.82821064635341e-01 1.13555603104327e-01 + 1.92853923563870e-01 1.15423555151864e-01 + 2.03269600951114e-01 1.17157630427070e-01 + 2.14073179855890e-01 1.18749830729886e-01 + 2.25269010690139e-01 1.20195797831111e-01 + 2.36862049700001e-01 1.21469516142441e-01 + 2.48856367816239e-01 1.22558448114212e-01 + 2.61254812509487e-01 1.23459965496932e-01 + 2.74060002850408e-01 1.24157250891336e-01 + 2.87274098574441e-01 1.24634125868712e-01 + 3.00897343465281e-01 1.24885240572198e-01 + 3.14930111913273e-01 1.24938181609379e-01 + 3.29371692980750e-01 1.24724549122169e-01 + 3.44221719292070e-01 1.24307490886237e-01 + 3.59478108674937e-01 1.23567755868112e-01 + 3.75139792148706e-01 1.22456688258022e-01 + 3.91203993073507e-01 1.21086123045838e-01 + 4.07669307000040e-01 1.19470016205814e-01 + 4.24531484406341e-01 1.17601586965184e-01 + 4.41786477980222e-01 1.15477530519042e-01 + 4.59430437714005e-01 1.13109140186475e-01 + 4.77458608360058e-01 1.10499382552401e-01 + 4.95862911928271e-01 1.07640323375764e-01 + 5.14640507672017e-01 1.04560841932114e-01 + 5.33783302980021e-01 1.01258821965706e-01 + 5.53283842708155e-01 9.77447261984488e-02 + 5.73132001488757e-01 9.40188334708139e-02 + 5.93318858507625e-01 9.00923641140249e-02 + 6.13834782021916e-01 8.59783693040786e-02 + 6.34666851564916e-01 8.16779614146220e-02 + 6.55808135409155e-01 7.72277953373070e-02 + 6.77245516640299e-01 7.26370604981205e-02 + 6.98969133928812e-01 6.79347164847326e-02 + 7.20963718956045e-01 6.31306748127620e-02 + 7.43213415006638e-01 5.82344583458571e-02 + 7.65709042197842e-01 5.32923633965684e-02 + 7.88431943052315e-01 4.83106536849915e-02 + 8.11365220544129e-01 4.33078905252115e-02 + 8.34492827307227e-01 3.83106490888924e-02 + 8.57792501162961e-01 3.33197297171255e-02 + 8.81244404698330e-01 2.83510461535743e-02 + 9.04830264085222e-01 2.34312170392390e-02 + 9.28525421748544e-01 1.84474300171901e-02 + 9.52306890313906e-01 1.35331900349642e-02 + 9.76140104343009e-01 8.66673115983542e-03 + 1.00000000000000e+00 3.87126252611321e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF33_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF33_Coords.txt new file mode 100644 index 00000000..b9423263 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF33_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -2.28655225865229e-03 + 9.75721322236667e-01 9.54369910662247e-04 + 9.51382552729723e-01 3.40062648464338e-03 + 9.27029635765017e-01 4.98402404923701e-03 + 9.02694326378763e-01 5.80229446998580e-03 + 8.78443210693472e-01 5.67721442450712e-03 + 8.54342403026775e-01 4.60294687831478e-03 + 8.30446767419120e-01 2.63556530921125e-03 + 8.06805212281844e-01 -2.64521613333467e-04 + 7.83474088117097e-01 -3.87183829866023e-03 + 7.60501446586731e-01 -8.23366950983079e-03 + 7.37915560591130e-01 -1.32586308899571e-02 + 7.15723961092165e-01 -1.88031588415209e-02 + 6.93931617754691e-01 -2.47620843345338e-02 + 6.72540754883845e-01 -3.10449767263213e-02 + 6.51540239804918e-01 -3.75351809762991e-02 + 6.30914414988264e-01 -4.41218961195991e-02 + 6.10643145691772e-01 -5.06942786651510e-02 + 5.90712421336183e-01 -5.71673404441778e-02 + 5.71107681907586e-01 -6.34572546666489e-02 + 5.51818055114220e-01 -6.94905146364697e-02 + 5.32838613759226e-01 -7.52151446077274e-02 + 5.14165414540733e-01 -8.05796028377901e-02 + 4.95803314834020e-01 -8.55594122633099e-02 + 4.77752551409938e-01 -9.01048489359325e-02 + 4.60018749447408e-01 -9.41869968196246e-02 + 4.42612079355789e-01 -9.77951900440706e-02 + 4.25547662437493e-01 -1.00944814759997e-01 + 4.08837212799525e-01 -1.03640613622302e-01 + 3.92493652415712e-01 -1.05886738488532e-01 + 3.76528492360307e-01 -1.07211636249933e-01 + 3.60949900843970e-01 -1.08200452177207e-01 + 3.45767059621715e-01 -1.08866487516599e-01 + 3.30987243411618e-01 -1.09240098494128e-01 + 3.16615713527019e-01 -1.09325301058059e-01 + 3.02655652194061e-01 -1.09132271137352e-01 + 2.89109640703685e-01 -1.08728096905146e-01 + 2.75978893230466e-01 -1.08062939513131e-01 + 2.63261967951429e-01 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-2.28076710670178e-02 + 9.12533611217964e-03 -2.12752302423776e-02 + 7.86665839866362e-03 -1.97529224253015e-02 + 6.70648838310773e-03 -1.82611048523234e-02 + 5.57019533438140e-03 -1.68404046434988e-02 + 4.53928828027559e-03 -1.54472508602149e-02 + 3.65789923556567e-03 -1.40399679030097e-02 + 2.92233268602207e-03 -1.26182977298276e-02 + 2.30790798886780e-03 -1.12037228725835e-02 + 1.82632559853049e-03 -9.79683014056990e-03 + 1.45196812175709e-03 -8.41103294741395e-03 + 1.17729695183517e-03 -7.05431977643600e-03 + 9.57447062003629e-04 -5.74753485275153e-03 + 7.54538045914156e-04 -4.49489443321160e-03 + 5.56942091965416e-04 -3.29531027209919e-03 + 3.76510929500736e-04 -2.14721446682755e-03 + 1.97421137389531e-04 -1.04929408479184e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 1.86727960599474e-04 1.05119742180028e-03 + 3.47782885680907e-04 2.15329679105333e-03 + 4.88743997136262e-04 3.30691192824467e-03 + 6.44046918478388e-04 4.51326172867321e-03 + 7.96856091718265e-04 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2.79619901913054e-02 4.65009378367207e-02 + 3.06817525238990e-02 4.87334507715206e-02 + 3.35689382397854e-02 5.10035003460305e-02 + 3.66309243620996e-02 5.33078574713119e-02 + 3.98778330723144e-02 5.56434198461375e-02 + 4.33146604848859e-02 5.80095738215555e-02 + 4.69499540997345e-02 6.04023011915549e-02 + 5.07912499129358e-02 6.28228416360851e-02 + 5.48456984109971e-02 6.52686799327633e-02 + 5.91199447893122e-02 6.77379219746159e-02 + 6.36191013018946e-02 7.02298492739661e-02 + 6.83535185622459e-02 7.27382450203669e-02 + 7.33317334843500e-02 7.52593810076249e-02 + 7.85620269745329e-02 7.77898076298057e-02 + 8.40525795359661e-02 8.03258938552421e-02 + 8.98115451888031e-02 8.28618143251143e-02 + 9.58475819038157e-02 8.53963503793477e-02 + 1.02170018097144e-01 8.79247685797251e-02 + 1.08787696430036e-01 9.04390228306913e-02 + 1.15709080969071e-01 9.29282334192782e-02 + 1.22942114481263e-01 9.53904471555562e-02 + 1.30495703056108e-01 9.78109836205552e-02 + 1.38378815114101e-01 1.00188606047808e-01 + 1.46600878757831e-01 1.02533433136919e-01 + 1.55169394551765e-01 1.04850159176791e-01 + 1.64092161704748e-01 1.07071451352010e-01 + 1.73375419863325e-01 1.09232608947482e-01 + 1.83028050193364e-01 1.11292438594720e-01 + 1.93057015771637e-01 1.13235367534031e-01 + 2.03468669577486e-01 1.15050867107640e-01 + 2.14267997351939e-01 1.16734080920269e-01 + 2.25459317366355e-01 1.18283114969957e-01 + 2.37048071454509e-01 1.19656437557375e-01 + 2.49038242774790e-01 1.20842827567519e-01 + 2.61432566427715e-01 1.21843770390964e-01 + 2.74233626631712e-01 1.22645068713666e-01 + 2.87443539111396e-01 1.23238668086382e-01 + 3.01062648743588e-01 1.23595670037009e-01 + 3.15091321683857e-01 1.23760249190434e-01 + 3.29528738968683e-01 1.23670137401317e-01 + 3.44374484106669e-01 1.23376864974725e-01 + 3.59626559114318e-01 1.22734960936677e-01 + 3.75283755516390e-01 1.21656569386618e-01 + 3.91343290185795e-01 1.20312635556553e-01 + 4.07803715029528e-01 1.18716514016919e-01 + 4.24661119620287e-01 1.16872770447226e-01 + 4.41910840883947e-01 1.14758541677097e-01 + 4.59549630858158e-01 1.12402949205246e-01 + 4.77572128951709e-01 1.09793886614310e-01 + 4.95970813541164e-01 1.06935937559023e-01 + 5.14743047705367e-01 1.03862396910533e-01 + 5.33880043208681e-01 1.00556913677013e-01 + 5.53374719761819e-01 9.70371632564740e-02 + 5.73217030908595e-01 9.33047646647311e-02 + 5.93397896215123e-01 8.93677900095761e-02 + 6.13907680091447e-01 8.52399214660122e-02 + 6.34733482572126e-01 8.09217580902728e-02 + 6.55868665599131e-01 7.64559455370953e-02 + 6.77300088565368e-01 7.18509007246176e-02 + 6.99017681232191e-01 6.71327286712102e-02 + 7.21006641599007e-01 6.23184999833508e-02 + 7.43250799821168e-01 5.74125565355643e-02 + 7.65741217996608e-01 5.24665225951827e-02 + 7.88459259864114e-01 4.74866679652408e-02 + 8.11388065298306e-01 4.24922741140753e-02 + 8.34511585139977e-01 3.75111330417436e-02 + 8.57807428038287e-01 3.25410811039965e-02 + 8.81255771974737e-01 2.75988870994086e-02 + 9.04838325774436e-01 2.27117117155849e-02 + 9.28530536924305e-01 1.77146083846230e-02 + 9.52309497234048e-01 1.28189790485560e-02 + 9.76140986286482e-01 7.99184030275693e-03 + 1.00000000000000e+00 3.26330481060804e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF34_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF34_Coords.txt new file mode 100644 index 00000000..c05fadf6 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF34_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -1.70008727284656e-03 + 9.75757442999300e-01 1.33962719268066e-03 + 9.51461656923270e-01 3.63790368313023e-03 + 9.27156563425510e-01 5.13461899761970e-03 + 9.02871415702250e-01 5.91677007157440e-03 + 8.78670756967060e-01 5.80682169167163e-03 + 8.54618897859540e-01 4.78690419537126e-03 + 8.30769634867738e-01 2.88254741956116e-03 + 8.07170544417778e-01 1.04244936265663e-04 + 7.83875798385858e-01 -3.36551974556091e-03 + 7.60931609682103e-01 -7.55459681442540e-03 + 7.38364835189792e-01 -1.23610853231397e-02 + 7.16185014741362e-01 -1.76600142761889e-02 + 6.94398481382825e-01 -2.33572806053302e-02 + 6.73008809033862e-01 -2.93710695222275e-02 + 6.52006840571961e-01 -3.55922059449307e-02 + 6.31378808627765e-01 -4.19157653626782e-02 + 6.11106786728224e-01 -4.82376039293054e-02 + 5.91178006848906e-01 -5.44758149661271e-02 + 5.71578610355932e-01 -6.05472940574775e-02 + 5.52297714509135e-01 -6.63758172647655e-02 + 5.33330934484040e-01 -7.19123387507361e-02 + 5.14674758868616e-01 -7.71081082224122e-02 + 4.96333345549048e-01 -8.19364608710434e-02 + 4.78305605079570e-01 -8.63388358753557e-02 + 4.60596268702772e-01 -9.02814584330476e-02 + 4.43215376002535e-01 -9.37539916233154e-02 + 4.26177203738470e-01 -9.67668994737366e-02 + 4.09493581572670e-01 -9.93284876266198e-02 + 3.93177212211695e-01 -1.01446517921001e-01 + 3.77239690656980e-01 -1.02763683890849e-01 + 3.61689141090763e-01 -1.03740185946740e-01 + 3.46534279624567e-01 -1.04386654177307e-01 + 3.31782356924523e-01 -1.04740182346232e-01 + 3.17438335448004e-01 -1.04804601563118e-01 + 3.03505300915573e-01 -1.04579097923195e-01 + 2.89985587225545e-01 -1.04161715234230e-01 + 2.76880188041674e-01 -1.03483641046245e-01 + 2.64187594420022e-01 -1.02612554220761e-01 + 2.51906565977157e-01 -1.01557581125237e-01 + 2.40033534758348e-01 -1.00341184000335e-01 + 2.28564652376948e-01 -9.89747608677339e-02 + 2.17495869717138e-01 -9.74716438262469e-02 + 2.06821810909897e-01 -9.58460632451405e-02 + 1.96535117524443e-01 -9.41198574617439e-02 + 1.86631680042317e-01 -9.22895977323459e-02 + 1.77101547822257e-01 -9.03780563907554e-02 + 1.67938744850930e-01 -8.83960612620546e-02 + 1.59134587680803e-01 -8.63561975718048e-02 + 1.50680591634610e-01 -8.42667238316057e-02 + 1.42567511727181e-01 -8.21359461571351e-02 + 1.34784707076311e-01 -7.99833590311928e-02 + 1.27324523915072e-01 -7.78128295807883e-02 + 1.20178613440043e-01 -7.56261072457596e-02 + 1.13336050508565e-01 -7.34344201131452e-02 + 1.06787402641099e-01 -7.12442169048557e-02 + 1.00524992169236e-01 -6.90530235979911e-02 + 9.45371078039178e-02 -6.68732086233714e-02 + 8.88139666336077e-02 -6.47101174450762e-02 + 8.33482439442156e-02 -6.25649981734568e-02 + 7.81312141944236e-02 -6.04392721216312e-02 + 7.31518173066822e-02 -5.83997350046384e-02 + 6.84026974561646e-02 -5.64218355327067e-02 + 6.38771791745571e-02 -5.44651326155087e-02 + 5.95661584569183e-02 -5.25323385718064e-02 + 5.54595314931183e-02 -5.06275646908205e-02 + 5.15494413221366e-02 -4.87504519943854e-02 + 4.78301638512260e-02 -4.68991687937419e-02 + 4.42947799040294e-02 -4.50720425614403e-02 + 4.09361595254644e-02 -4.32708658253099e-02 + 3.77495221092536e-02 -4.14961810479447e-02 + 3.47270500666477e-02 -3.97496400899892e-02 + 3.18643051622500e-02 -3.80288209444548e-02 + 2.91562842903780e-02 -3.63344862352920e-02 + 2.65938508565125e-02 -3.46683323951838e-02 + 2.41761809199326e-02 -3.30280287657854e-02 + 2.18957353818106e-02 -3.14110428164351e-02 + 1.97433603412845e-02 -2.98245286712917e-02 + 1.77155058661606e-02 -2.82660102882950e-02 + 1.58222892232330e-02 -2.67255643170919e-02 + 1.40578525293395e-02 -2.52017457836673e-02 + 1.24112060980532e-02 -2.37092093488654e-02 + 1.08759783397775e-02 -2.22444625557423e-02 + 9.46232665461570e-03 -2.07921683896738e-02 + 8.16948372733245e-03 -1.93421233126744e-02 + 6.97531793748111e-03 -1.79183527493840e-02 + 5.81014322923250e-03 -1.65565928866959e-02 + 4.74819136453736e-03 -1.52227999669970e-02 + 3.83529204644056e-03 -1.38668516263032e-02 + 3.07000967477440e-03 -1.24862432090756e-02 + 2.42804184993088e-03 -1.11050074170431e-02 + 1.92254892763096e-03 -9.72240141555189e-03 + 1.52976489250848e-03 -8.35345985101848e-03 + 1.24112548297123e-03 -7.00747049795239e-03 + 1.02028728572417e-03 -5.71003179554596e-03 + 8.13480608339388e-04 -4.46566226585669e-03 + 6.04648434499428e-04 -3.27385095072104e-03 + 4.09850292628465e-04 -2.13312087853641e-03 + 2.14328089277376e-04 -1.04229296499157e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.03645492746842e-04 1.04445500936502e-03 + 3.80229598179513e-04 2.14010633957589e-03 + 5.37842002699659e-04 3.28725331497461e-03 + 7.05051456767521e-04 4.48706951755623e-03 + 8.64984648405100e-04 5.74111366019337e-03 + 1.03196338113797e-03 7.04881664992474e-03 + 1.23142203832641e-03 8.41106345925421e-03 + 1.48378549243307e-03 9.82185370098230e-03 + 1.83974087515607e-03 1.12610259945533e-02 + 2.30262304143410e-03 1.27345841629370e-02 + 2.83716087217056e-03 1.42453752589016e-02 + 3.47001113240836e-03 1.57793255881880e-02 + 4.22204906364905e-03 1.73359398975203e-02 + 5.05926693832384e-03 1.89315418368386e-02 + 5.97298719910323e-03 2.05916615295347e-02 + 6.97418957300841e-03 2.22903748877105e-02 + 8.10010022115337e-03 2.40186683432688e-02 + 9.34461449362398e-03 2.57779865658367e-02 + 1.06990338921582e-02 2.75789759301495e-02 + 1.21492475338527e-02 2.94260794391358e-02 + 1.37246538832546e-02 3.13095369631231e-02 + 1.54293155280999e-02 3.32252553088824e-02 + 1.72640936157335e-02 3.51802627703454e-02 + 1.92271940049126e-02 3.71739732807179e-02 + 2.13338360956640e-02 3.92022400836712e-02 + 2.35888755558957e-02 4.12640455183332e-02 + 2.59979356742100e-02 4.33651778556460e-02 + 2.85698634157347e-02 4.55004902421537e-02 + 3.13087537708386e-02 4.76687098538121e-02 + 3.42142595528832e-02 4.98735595229720e-02 + 3.72938174470553e-02 5.21114442912126e-02 + 4.05570831285218e-02 5.43804844261640e-02 + 4.40092964474428e-02 5.66796624896247e-02 + 4.76589220120135e-02 5.90054002590296e-02 + 5.15128347795698e-02 6.13611408286700e-02 + 5.55783143369923e-02 6.37441523294786e-02 + 5.98622185098501e-02 6.61520261326188e-02 + 6.43700175836475e-02 6.85831105728570e-02 + 6.91117951903834e-02 7.10321918442136e-02 + 7.40960491250514e-02 7.34958426806031e-02 + 7.93310558903069e-02 7.59708755960914e-02 + 8.48250103100324e-02 7.84538833316611e-02 + 9.05862734061244e-02 8.09381242245646e-02 + 9.66230067848283e-02 8.34253209857669e-02 + 1.02944328376156e-01 8.59124532744344e-02 + 1.09559298849723e-01 8.83907366439924e-02 + 1.16477003230928e-01 9.08462957949981e-02 + 1.23705092005791e-01 9.32790628489261e-02 + 1.31253064817888e-01 9.56703973145901e-02 + 1.39129163642365e-01 9.80253083026896e-02 + 1.47342115570675e-01 1.00371156174573e-01 + 1.55899994279582e-01 1.02723688074117e-01 + 1.64813403330152e-01 1.04973631446205e-01 + 1.74084388100436e-01 1.07181670251407e-01 + 1.83724165707002e-01 1.09292179907538e-01 + 1.93740037514196e-01 1.11287554744272e-01 + 2.04138159567124e-01 1.13159291588675e-01 + 2.14923190316235e-01 1.14906164223987e-01 + 2.26099339940529e-01 1.16528369574661e-01 + 2.37673683359147e-01 1.17967604176458e-01 + 2.49649908542195e-01 1.19212608572790e-01 + 2.62030372676954e-01 1.20267988601237e-01 + 2.74817542769904e-01 1.21121595128239e-01 + 2.88013386532346e-01 1.21775488378959e-01 + 3.01618588828562e-01 1.22165884455076e-01 + 3.15633488119645e-01 1.22351219591036e-01 + 3.30056902139094e-01 1.22278999395077e-01 + 3.44888249213742e-01 1.21964814357112e-01 + 3.60125814496415e-01 1.21329217314464e-01 + 3.75767920375995e-01 1.20284008978546e-01 + 3.91811761908143e-01 1.18964810312656e-01 + 4.08255744221217e-01 1.17384005118637e-01 + 4.25097097301065e-01 1.15565287541140e-01 + 4.42329087197514e-01 1.13453519172657e-01 + 4.59950490693772e-01 1.11107280207411e-01 + 4.77953911360686e-01 1.08489236240058e-01 + 4.96333698697975e-01 1.05625395680430e-01 + 5.15087901272280e-01 1.02556023803917e-01 + 5.34205391385655e-01 9.92406266176922e-02 + 5.53680349427449e-01 9.57092689422690e-02 + 5.73502994329569e-01 9.19658115476644e-02 + 5.93663708839333e-01 8.80131118475106e-02 + 6.14152844428511e-01 8.38654581538432e-02 + 6.34957570079735e-01 7.95231147981840e-02 + 6.56072235378048e-01 7.50379434783887e-02 + 6.77483620034969e-01 7.04171635595818e-02 + 6.99180951227209e-01 6.56816702998434e-02 + 7.21150995233810e-01 6.08606795062229e-02 + 7.43376529121406e-01 5.59498869263449e-02 + 7.65849428795947e-01 5.10088747184360e-02 + 7.88551129348430e-01 4.60441709795809e-02 + 8.11464894754138e-01 4.10762688533146e-02 + 8.34574669823296e-01 3.61343057108217e-02 + 8.57857628784579e-01 3.12117165661705e-02 + 8.81294001392915e-01 2.63264549411032e-02 + 9.04865438134263e-01 2.15062058228121e-02 + 9.28547739830810e-01 1.66251759843438e-02 + 9.52318264597199e-01 1.18614383546103e-02 + 9.76143952360734e-01 7.17598522379954e-03 + 1.00000000000000e+00 2.60229290134914e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF35_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF35_Coords.txt new file mode 100644 index 00000000..7ba442f6 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF35_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -1.16352604390801e-03 + 9.75826236205482e-01 1.66795337094237e-03 + 9.51612313517979e-01 3.81662415801630e-03 + 9.27398301420009e-01 5.23366586158571e-03 + 9.03208688269478e-01 5.99117916495978e-03 + 8.79104126491238e-01 5.89275019763225e-03 + 8.55145491559466e-01 4.92762323760028e-03 + 8.31384546772790e-01 3.11888496576622e-03 + 8.07866331746746e-01 5.27330687279865e-04 + 7.84640869091193e-01 -2.74497194247924e-03 + 7.61750869751803e-01 -6.69416802683588e-03 + 7.39220493759704e-01 -1.12048068679547e-02 + 7.17063106908823e-01 -1.61782325079694e-02 + 6.95287638850399e-01 -2.15329223588853e-02 + 6.73900233890368e-01 -2.71970224953806e-02 + 6.52895497411758e-01 -3.30720998985836e-02 + 6.32263261918992e-01 -3.90611716093124e-02 + 6.11989806661655e-01 -4.50697592290980e-02 + 5.92064730102734e-01 -5.10200186999722e-02 + 5.72475509410190e-01 -5.68299522020147e-02 + 5.53211241944514e-01 -6.24206160851780e-02 + 5.34268575847668e-01 -6.77461185437110e-02 + 5.15644822256324e-01 -7.27613239384657e-02 + 4.97342806856187e-01 -7.74357943659871e-02 + 4.79358914377381e-01 -8.17011100065960e-02 + 4.61696173530714e-01 -8.55173779836949e-02 + 4.44364374738552e-01 -8.88743560807564e-02 + 4.27376186300355e-01 -9.17755292203566e-02 + 4.10743657956769e-01 -9.42323530040160e-02 + 3.94479074812476e-01 -9.62586481962852e-02 + 3.78594191711050e-01 -9.77004324381062e-02 + 3.63097048981117e-01 -9.87888690044308e-02 + 3.47995475900525e-01 -9.95324519019542e-02 + 3.33296677327669e-01 -9.99752963965443e-02 + 3.19005046538691e-01 -1.00123283749691e-01 + 3.05123485456033e-01 -9.99613140111835e-02 + 2.91653856810438e-01 -9.96234765367142e-02 + 2.78596734295398e-01 -9.90207472373655e-02 + 2.65950481132839e-01 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-2.18855893092176e-02 + 1.01041364664171e-02 -2.04857690534728e-02 + 8.74622474147678e-03 -1.90827276884963e-02 + 7.48731285713604e-03 -1.77029520939151e-02 + 6.26713205783067e-03 -1.63790038342829e-02 + 5.14605430818425e-03 -1.50830855579442e-02 + 4.17314261559750e-03 -1.37596436602635e-02 + 3.35126546217235e-03 -1.24048359691523e-02 + 2.65684082512612e-03 -1.10444047340198e-02 + 2.10580949124927e-03 -9.67685363872774e-03 + 1.67793145657213e-03 -8.31830149342973e-03 + 1.36268906531944e-03 -6.97888547622378e-03 + 1.12000837452246e-03 -5.68716353117902e-03 + 8.93458951997472e-04 -4.44784411422790e-03 + 6.64446509037175e-04 -3.26077450076612e-03 + 4.46845666214424e-04 -2.12453374924321e-03 + 2.29527828984537e-04 -1.03802680781396e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.18935685969158e-04 1.04034841829192e-03 + 4.14490203079302e-04 2.13207604506963e-03 + 5.96662999749155e-04 3.27528752912841e-03 + 7.82797939374329e-04 4.47112808142116e-03 + 9.61960049506389e-04 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2.97275783977332e-02 4.48577375190175e-02 + 3.25028987144580e-02 4.69831129684012e-02 + 3.54432956781012e-02 4.91443274381631e-02 + 3.85563196022324e-02 5.13375161931052e-02 + 4.18507376850831e-02 5.35616210239821e-02 + 4.53322539796522e-02 5.58153428939390e-02 + 4.90091752240582e-02 5.80953712699467e-02 + 5.28871174051451e-02 6.04066714775590e-02 + 5.69736059857924e-02 6.27463696974772e-02 + 6.12759037528830e-02 6.51116492906241e-02 + 6.58001628749262e-02 6.75002020335691e-02 + 7.05559585086778e-02 6.99075048969030e-02 + 7.55517139456997e-02 7.23303122679040e-02 + 8.07956973017088e-02 7.47655896051978e-02 + 8.62961306748632e-02 7.72100782694164e-02 + 9.20617693288342e-02 7.96563540794358e-02 + 9.80998295269478e-02 8.21081713779918e-02 + 1.04419028321310e-01 8.45637420885748e-02 + 1.11028841585804e-01 8.70137658341035e-02 + 1.17939536982759e-01 8.94421759352875e-02 + 1.25158208339224e-01 9.18501860420740e-02 + 1.32695485742464e-01 9.42162027144823e-02 + 1.40558227628046e-01 9.65497949258293e-02 + 1.48753825988161e-01 9.88850780420452e-02 + 1.57291446011204e-01 1.01238013059508e-01 + 1.66187032241270e-01 1.03478709746172e-01 + 1.75434641931136e-01 1.05693670499823e-01 + 1.85049941093962e-01 1.07812899921013e-01 + 1.95040875374152e-01 1.09816836982480e-01 + 2.05413225748941e-01 1.11699020566677e-01 + 2.16171027332872e-01 1.13462933416945e-01 + 2.27318284439415e-01 1.15110317869378e-01 + 2.38865182253667e-01 1.16566027328053e-01 + 2.50814846549728e-01 1.17818328772653e-01 + 2.63168914766428e-01 1.18874920439618e-01 + 2.75929630676144e-01 1.19726174426695e-01 + 2.89098680093855e-01 1.20386012684450e-01 + 3.02677395401382e-01 1.20750679458112e-01 + 3.16666062314764e-01 1.20892381510022e-01 + 3.31062806644756e-01 1.20771822231848e-01 + 3.45866732123965e-01 1.20358172784995e-01 + 3.61076663147858e-01 1.19670395516332e-01 + 3.76690028620272e-01 1.18632356161148e-01 + 3.92703982045185e-01 1.17312914760594e-01 + 4.09116649006107e-01 1.15723374511861e-01 + 4.25927431444056e-01 1.13909960040119e-01 + 4.43125651355832e-01 1.11780533573370e-01 + 4.60713941720601e-01 1.09427503349694e-01 + 4.78681028787433e-01 1.06784086652576e-01 + 4.97024825672978e-01 1.03901995378440e-01 + 5.15744686478415e-01 1.00829014754215e-01 + 5.34825027921222e-01 9.74960022006922e-02 + 5.54262431395570e-01 9.39479504186166e-02 + 5.74047621273907e-01 9.01913350056972e-02 + 5.94169957914115e-01 8.62230063908930e-02 + 6.14619768146589e-01 8.20573000093964e-02 + 6.35384352267882e-01 7.76948591470723e-02 + 6.56459940862454e-01 7.31971132724339e-02 + 6.77833161885944e-01 6.85700238894307e-02 + 6.99491904419003e-01 6.38277709277193e-02 + 7.21425921581938e-01 5.90139861932156e-02 + 7.43615984798529e-01 5.41143101961112e-02 + 7.66055519899444e-01 4.91962058582531e-02 + 7.88726097868356e-01 4.42668669239231e-02 + 8.11611219034432e-01 3.93482102125072e-02 + 8.34694816722482e-01 3.44699290009385e-02 + 8.57953237792765e-01 2.96211418843023e-02 + 8.81366810604441e-01 2.48208236675982e-02 + 9.04917074534596e-01 2.00967093307105e-02 + 9.28580503344309e-01 1.53933948841804e-02 + 9.52334962334925e-01 1.08181547894991e-02 + 9.76149601348813e-01 6.32737840061601e-03 + 1.00000000000000e+00 1.95682769991448e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF36_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF36_Coords.txt new file mode 100644 index 00000000..46bf8fdb --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF36_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -7.29419189595606e-04 + 9.75915770699515e-01 1.91249465128369e-03 + 9.51808393374241e-01 3.92801765257105e-03 + 9.27712923898406e-01 5.28058205482929e-03 + 9.03647649183407e-01 6.02611534062702e-03 + 8.79668157784876e-01 5.93369316895642e-03 + 8.55830854302391e-01 5.01729338014448e-03 + 8.32184855834527e-01 3.31715343145611e-03 + 8.08771900332813e-01 9.10324330805802e-04 + 7.85636610128757e-01 -2.15320157523943e-03 + 7.62817138354366e-01 -5.84613854585871e-03 + 7.40334135082350e-01 -1.00471977439171e-02 + 7.18205945603090e-01 -1.46862635999984e-02 + 6.96444879054669e-01 -1.96928550706371e-02 + 6.75060425105821e-01 -2.50040349649066e-02 + 6.54052086047983e-01 -3.05331519068835e-02 + 6.33414379628432e-01 -3.61915187684513e-02 + 6.13139058853086e-01 -4.18952946150173e-02 + 5.93218802172994e-01 -4.75707892314447e-02 + 5.73642825304853e-01 -5.31372760744497e-02 + 5.54400199710125e-01 -5.85138129187541e-02 + 5.35488917938631e-01 -6.36570901865027e-02 + 5.16907361675811e-01 -6.85256085948266e-02 + 4.98656622745809e-01 -7.30842665590296e-02 + 4.80729798513666e-01 -7.72561882435040e-02 + 4.63127701841708e-01 -8.09954861801213e-02 + 4.45859798868093e-01 -8.42917076265271e-02 + 4.28936664478215e-01 -8.71407575833897e-02 + 4.12370634845388e-01 -8.95559092428311e-02 + 3.96173451564625e-01 -9.15539874697587e-02 + 3.80357077514361e-01 -9.31232055630836e-02 + 3.64929443887577e-01 -9.43349182124982e-02 + 3.49897225746343e-01 -9.51944277905604e-02 + 3.35267568330188e-01 -9.57507180586334e-02 + 3.21044124124761e-01 -9.60110700205248e-02 + 3.07229555838880e-01 -9.59456677056186e-02 + 2.93825112977767e-01 -9.57210149294118e-02 + 2.80830822642781e-01 -9.52294539922503e-02 + 2.68244881679471e-01 -9.45350089350621e-02 + 2.56064470917142e-01 -9.36657880458372e-02 + 2.44285335780625e-01 -9.26430628818212e-02 + 2.32903937940105e-01 -9.14690258488800e-02 + 2.21914524904501e-01 -9.01669243973229e-02 + 2.11310663292912e-01 -8.87541232371338e-02 + 2.01085586759147e-01 -8.72436511767301e-02 + 1.91233849306635e-01 -8.56366026641871e-02 + 1.81747208324209e-01 -8.39458714430274e-02 + 1.72617697925855e-01 -8.21892402390199e-02 + 1.63836073935780e-01 -8.03812614259989e-02 + 1.55395083642858e-01 -7.85239554053773e-02 + 1.47285649578784e-01 -7.66251141830917e-02 + 1.39496596044998e-01 -7.47054760953099e-02 + 1.32019513430619e-01 -7.27704440051866e-02 + 1.24847290909011e-01 -7.08178850820173e-02 + 1.17969456169464e-01 -6.88581443017359e-02 + 1.11376744913913e-01 -6.68975858111069e-02 + 1.05062219859245e-01 -6.49323140693849e-02 + 9.90152852057825e-02 -6.29730846588107e-02 + 9.32266946462527e-02 -6.10246519345936e-02 + 8.76883756833979e-02 -5.90896477455711e-02 + 8.23918799049788e-02 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2.34371671028459e-02 + 9.04984279411852e-01 1.88185087254521e-02 + 9.28623145121989e-01 1.42812227847677e-02 + 9.52356694473630e-01 9.88520564797795e-03 + 9.76156953517981e-01 5.58116316342507e-03 + 1.00000000000000e+00 1.40781838692117e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF37_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF37_Coords.txt new file mode 100644 index 00000000..bba4831b --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF37_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -4.49626526216799e-04 + 9.75993006946222e-01 2.05848660835095e-03 + 9.51977540163041e-01 3.98167290739308e-03 + 9.27984330573828e-01 5.29267745574830e-03 + 9.04026315459564e-01 6.03506973227252e-03 + 8.80154715067815e-01 5.94428938366653e-03 + 8.56422077232372e-01 5.06171539032128e-03 + 8.32875236327564e-01 3.44821301238136e-03 + 8.09553082149713e-01 1.16895433834449e-03 + 7.86495578521493e-01 -1.73718424367720e-03 + 7.63736946811802e-01 -5.23353787688778e-03 + 7.41294809254559e-01 -9.20055844303472e-03 + 7.19191806664689e-01 -1.35902529656892e-02 + 6.97443163468759e-01 -1.83393325613028e-02 + 6.76061255187145e-01 -2.33907812730678e-02 + 6.55049808391880e-01 -2.86671489289203e-02 + 6.34407382519169e-01 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2.24955104221916e-02 + 9.05042253185376e-01 1.79592199578819e-02 + 9.28659929725470e-01 1.35286467790738e-02 + 9.52375441536923e-01 9.25274519100639e-03 + 9.76163295810500e-01 5.07654643028011e-03 + 1.00000000000000e+00 1.04191728915796e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF38_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF38_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF38_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 -3.34644442304210e-02 + 6.14445718488537e-01 -3.88868243087427e-02 + 5.94530941842471e-01 -4.43132611654412e-02 + 5.74970022740498e-01 -4.96643666397068e-02 + 5.55752003197788e-01 -5.48579023094515e-02 + 5.36876404308979e-01 -5.98525300304434e-02 + 5.18342824936104e-01 -6.46102084095419e-02 + 5.00150385563215e-01 -6.90906898681219e-02 + 4.82288445935981e-01 -7.32102556940118e-02 + 4.64755299574327e-01 -7.69174493160327e-02 + 4.47560043916586e-01 -8.02013672216798e-02 + 4.30710873709413e-01 -8.30502485164628e-02 + 4.14220450790071e-01 -8.54779875163164e-02 + 3.98099898802043e-01 -8.75003551684143e-02 + 3.82361417152145e-01 -8.91539118487549e-02 + 3.67012812949938e-01 -9.04577352136744e-02 + 3.52059448954428e-01 -9.14125244130858e-02 + 3.37508402620579e-01 -9.20698975569944e-02 + 3.23362484181096e-01 -9.24370482908363e-02 + 3.09624084367261e-01 -9.24697923842373e-02 + 2.96293755468272e-01 -9.23622670606858e-02 + 2.83370903129312e-01 -9.19897555434183e-02 + 2.70853535031793e-01 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-2.16754212282863e-02 + 1.18891791905238e-02 -2.03070715945921e-02 + 1.03502939408908e-02 -1.89320620321851e-02 + 8.91130605466057e-03 -1.75783863139938e-02 + 7.53813877740335e-03 -1.62767162061906e-02 + 6.25261631407701e-03 -1.50030050459626e-02 + 5.11279434609420e-03 -1.36984926934841e-02 + 4.13351214596566e-03 -1.23586032117553e-02 + 3.29319124926354e-03 -1.10101245850993e-02 + 2.61550555648146e-03 -9.65116862965519e-03 + 2.09002183330755e-03 -8.29851601144447e-03 + 1.70078951843963e-03 -6.96281267583815e-03 + 1.36265166348109e-03 -5.67431295008859e-03 + 1.05977091812036e-03 -4.43783511622449e-03 + 7.76752295586629e-04 -3.25343117981278e-03 + 5.09088367705372e-04 -2.11971200576328e-03 + 2.51457101720442e-04 -1.03563109330527e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.41152507493868e-04 1.03804336890630e-03 + 4.71263736944646e-04 2.12757058293535e-03 + 6.99943594043346e-04 3.26857529570577e-03 + 9.32193128484313e-04 4.46218636779492e-03 + 1.17467942772895e-03 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3.29474897596453e-02 4.44785420770728e-02 + 3.58241314284824e-02 4.65778377875867e-02 + 3.88615699902796e-02 4.87123968511837e-02 + 4.20676717891717e-02 5.08781772356130e-02 + 4.54487329341993e-02 5.30746242381647e-02 + 4.90117485491485e-02 5.53002611029898e-02 + 5.27645862937288e-02 5.75519273923613e-02 + 5.67093606250863e-02 5.98355421876917e-02 + 6.08542808522407e-02 6.21481464820482e-02 + 6.52077360665248e-02 6.44866424610369e-02 + 6.97777749333136e-02 6.68483047653571e-02 + 7.45725584053168e-02 6.92290421276930e-02 + 7.96003025603602e-02 7.16257099944468e-02 + 8.48692521878683e-02 7.40353559775043e-02 + 9.03877052429679e-02 7.64548116524863e-02 + 9.61655134799091e-02 7.88762011581258e-02 + 1.02207263913494e-01 8.13045515555609e-02 + 1.08520558648419e-01 8.37388705427050e-02 + 1.15116028351370e-01 8.61695316478935e-02 + 1.22007229910574e-01 8.85790359587486e-02 + 1.29199708937344e-01 9.09693898928607e-02 + 1.36707239581636e-01 9.33170443302486e-02 + 1.44532832289765e-01 9.56345442285116e-02 + 1.52680165789989e-01 9.79325041341286e-02 + 1.61161441053045e-01 1.00189166048500e-01 + 1.70007457308521e-01 1.02310587742487e-01 + 1.79190054721449e-01 1.04432905562834e-01 + 1.88737272862309e-01 1.06459673932072e-01 + 1.98658849288637e-01 1.08368456710055e-01 + 2.08959521814780e-01 1.10157093980485e-01 + 2.19641591893373e-01 1.11840420663148e-01 + 2.30708491271435e-01 1.13421765446694e-01 + 2.42179055605765e-01 1.14797531689102e-01 + 2.54054847054779e-01 1.15956061862792e-01 + 2.66335501246618e-01 1.16912330796287e-01 + 2.79022641080626e-01 1.17663923550265e-01 + 2.92117168343597e-01 1.18248653891892e-01 + 3.05622216334775e-01 1.18493312816741e-01 + 3.19537924072257e-01 1.18497489736340e-01 + 3.33860492946775e-01 1.18251006166221e-01 + 3.48588151721234e-01 1.17646648524711e-01 + 3.63721224567419e-01 1.16827356073084e-01 + 3.79254655371093e-01 1.15711829738200e-01 + 3.95185482070027e-01 1.14309376763544e-01 + 4.11511052759619e-01 1.12629630765949e-01 + 4.28236810162283e-01 1.10757309311154e-01 + 4.45341106820901e-01 1.08539918592541e-01 + 4.62837300814829e-01 1.06125215640029e-01 + 4.80703334536459e-01 1.03396855089698e-01 + 4.98947032463024e-01 1.00451779534968e-01 + 5.17571379732328e-01 9.73486814910668e-02 + 5.36548400903477e-01 9.39688774564715e-02 + 5.55881355199664e-01 9.03838060138069e-02 + 5.75562372757084e-01 8.66043381028199e-02 + 5.95577970398358e-01 8.26174413045570e-02 + 6.15918406419707e-01 7.84356567370351e-02 + 6.36571346336407e-01 7.40624490885372e-02 + 6.57538252289466e-01 6.95719746617823e-02 + 6.78805330161313e-01 6.49684751967319e-02 + 7.00356747433778e-01 6.02530296562983e-02 + 7.22190564422178e-01 5.54942107563349e-02 + 7.44281974327413e-01 5.06608414104289e-02 + 7.66628713730443e-01 4.58296525153133e-02 + 7.89212731568401e-01 4.10099912210156e-02 + 8.12018185533069e-01 3.62261968408074e-02 + 8.35028977005283e-01 3.15060199889171e-02 + 8.58219151715056e-01 2.68336443816806e-02 + 8.81569312265979e-01 2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF39_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF39_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF39_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 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2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF40_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF40_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF40_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 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9.56345442285116e-02 + 1.52680165789989e-01 9.79325041341286e-02 + 1.61161441053045e-01 1.00189166048500e-01 + 1.70007457308521e-01 1.02310587742487e-01 + 1.79190054721449e-01 1.04432905562834e-01 + 1.88737272862309e-01 1.06459673932072e-01 + 1.98658849288637e-01 1.08368456710055e-01 + 2.08959521814780e-01 1.10157093980485e-01 + 2.19641591893373e-01 1.11840420663148e-01 + 2.30708491271435e-01 1.13421765446694e-01 + 2.42179055605765e-01 1.14797531689102e-01 + 2.54054847054779e-01 1.15956061862792e-01 + 2.66335501246618e-01 1.16912330796287e-01 + 2.79022641080626e-01 1.17663923550265e-01 + 2.92117168343597e-01 1.18248653891892e-01 + 3.05622216334775e-01 1.18493312816741e-01 + 3.19537924072257e-01 1.18497489736340e-01 + 3.33860492946775e-01 1.18251006166221e-01 + 3.48588151721234e-01 1.17646648524711e-01 + 3.63721224567419e-01 1.16827356073084e-01 + 3.79254655371093e-01 1.15711829738200e-01 + 3.95185482070027e-01 1.14309376763544e-01 + 4.11511052759619e-01 1.12629630765949e-01 + 4.28236810162283e-01 1.10757309311154e-01 + 4.45341106820901e-01 1.08539918592541e-01 + 4.62837300814829e-01 1.06125215640029e-01 + 4.80703334536459e-01 1.03396855089698e-01 + 4.98947032463024e-01 1.00451779534968e-01 + 5.17571379732328e-01 9.73486814910668e-02 + 5.36548400903477e-01 9.39688774564715e-02 + 5.55881355199664e-01 9.03838060138069e-02 + 5.75562372757084e-01 8.66043381028199e-02 + 5.95577970398358e-01 8.26174413045570e-02 + 6.15918406419707e-01 7.84356567370351e-02 + 6.36571346336407e-01 7.40624490885372e-02 + 6.57538252289466e-01 6.95719746617823e-02 + 6.78805330161313e-01 6.49684751967319e-02 + 7.00356747433778e-01 6.02530296562983e-02 + 7.22190564422178e-01 5.54942107563349e-02 + 7.44281974327413e-01 5.06608414104289e-02 + 7.66628713730443e-01 4.58296525153133e-02 + 7.89212731568401e-01 4.10099912210156e-02 + 8.12018185533069e-01 3.62261968408074e-02 + 8.35028977005283e-01 3.15060199889171e-02 + 8.58219151715056e-01 2.68336443816806e-02 + 8.81569312265979e-01 2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF41_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF41_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF41_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 -3.34644442304210e-02 + 6.14445718488537e-01 -3.88868243087427e-02 + 5.94530941842471e-01 -4.43132611654412e-02 + 5.74970022740498e-01 -4.96643666397068e-02 + 5.55752003197788e-01 -5.48579023094515e-02 + 5.36876404308979e-01 -5.98525300304434e-02 + 5.18342824936104e-01 -6.46102084095419e-02 + 5.00150385563215e-01 -6.90906898681219e-02 + 4.82288445935981e-01 -7.32102556940118e-02 + 4.64755299574327e-01 -7.69174493160327e-02 + 4.47560043916586e-01 -8.02013672216798e-02 + 4.30710873709413e-01 -8.30502485164628e-02 + 4.14220450790071e-01 -8.54779875163164e-02 + 3.98099898802043e-01 -8.75003551684143e-02 + 3.82361417152145e-01 -8.91539118487549e-02 + 3.67012812949938e-01 -9.04577352136744e-02 + 3.52059448954428e-01 -9.14125244130858e-02 + 3.37508402620579e-01 -9.20698975569944e-02 + 3.23362484181096e-01 -9.24370482908363e-02 + 3.09624084367261e-01 -9.24697923842373e-02 + 2.96293755468272e-01 -9.23622670606858e-02 + 2.83370903129312e-01 -9.19897555434183e-02 + 2.70853535031793e-01 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-2.16754212282863e-02 + 1.18891791905238e-02 -2.03070715945921e-02 + 1.03502939408908e-02 -1.89320620321851e-02 + 8.91130605466057e-03 -1.75783863139938e-02 + 7.53813877740335e-03 -1.62767162061906e-02 + 6.25261631407701e-03 -1.50030050459626e-02 + 5.11279434609420e-03 -1.36984926934841e-02 + 4.13351214596566e-03 -1.23586032117553e-02 + 3.29319124926354e-03 -1.10101245850993e-02 + 2.61550555648146e-03 -9.65116862965519e-03 + 2.09002183330755e-03 -8.29851601144447e-03 + 1.70078951843963e-03 -6.96281267583815e-03 + 1.36265166348109e-03 -5.67431295008859e-03 + 1.05977091812036e-03 -4.43783511622449e-03 + 7.76752295586629e-04 -3.25343117981278e-03 + 5.09088367705372e-04 -2.11971200576328e-03 + 2.51457101720442e-04 -1.03563109330527e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.41152507493868e-04 1.03804336890630e-03 + 4.71263736944646e-04 2.12757058293535e-03 + 6.99943594043346e-04 3.26857529570577e-03 + 9.32193128484313e-04 4.46218636779492e-03 + 1.17467942772895e-03 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9.56345442285116e-02 + 1.52680165789989e-01 9.79325041341286e-02 + 1.61161441053045e-01 1.00189166048500e-01 + 1.70007457308521e-01 1.02310587742487e-01 + 1.79190054721449e-01 1.04432905562834e-01 + 1.88737272862309e-01 1.06459673932072e-01 + 1.98658849288637e-01 1.08368456710055e-01 + 2.08959521814780e-01 1.10157093980485e-01 + 2.19641591893373e-01 1.11840420663148e-01 + 2.30708491271435e-01 1.13421765446694e-01 + 2.42179055605765e-01 1.14797531689102e-01 + 2.54054847054779e-01 1.15956061862792e-01 + 2.66335501246618e-01 1.16912330796287e-01 + 2.79022641080626e-01 1.17663923550265e-01 + 2.92117168343597e-01 1.18248653891892e-01 + 3.05622216334775e-01 1.18493312816741e-01 + 3.19537924072257e-01 1.18497489736340e-01 + 3.33860492946775e-01 1.18251006166221e-01 + 3.48588151721234e-01 1.17646648524711e-01 + 3.63721224567419e-01 1.16827356073084e-01 + 3.79254655371093e-01 1.15711829738200e-01 + 3.95185482070027e-01 1.14309376763544e-01 + 4.11511052759619e-01 1.12629630765949e-01 + 4.28236810162283e-01 1.10757309311154e-01 + 4.45341106820901e-01 1.08539918592541e-01 + 4.62837300814829e-01 1.06125215640029e-01 + 4.80703334536459e-01 1.03396855089698e-01 + 4.98947032463024e-01 1.00451779534968e-01 + 5.17571379732328e-01 9.73486814910668e-02 + 5.36548400903477e-01 9.39688774564715e-02 + 5.55881355199664e-01 9.03838060138069e-02 + 5.75562372757084e-01 8.66043381028199e-02 + 5.95577970398358e-01 8.26174413045570e-02 + 6.15918406419707e-01 7.84356567370351e-02 + 6.36571346336407e-01 7.40624490885372e-02 + 6.57538252289466e-01 6.95719746617823e-02 + 6.78805330161313e-01 6.49684751967319e-02 + 7.00356747433778e-01 6.02530296562983e-02 + 7.22190564422178e-01 5.54942107563349e-02 + 7.44281974327413e-01 5.06608414104289e-02 + 7.66628713730443e-01 4.58296525153133e-02 + 7.89212731568401e-01 4.10099912210156e-02 + 8.12018185533069e-01 3.62261968408074e-02 + 8.35028977005283e-01 3.15060199889171e-02 + 8.58219151715056e-01 2.68336443816806e-02 + 8.81569312265979e-01 2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF42_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF42_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF42_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 -3.34644442304210e-02 + 6.14445718488537e-01 -3.88868243087427e-02 + 5.94530941842471e-01 -4.43132611654412e-02 + 5.74970022740498e-01 -4.96643666397068e-02 + 5.55752003197788e-01 -5.48579023094515e-02 + 5.36876404308979e-01 -5.98525300304434e-02 + 5.18342824936104e-01 -6.46102084095419e-02 + 5.00150385563215e-01 -6.90906898681219e-02 + 4.82288445935981e-01 -7.32102556940118e-02 + 4.64755299574327e-01 -7.69174493160327e-02 + 4.47560043916586e-01 -8.02013672216798e-02 + 4.30710873709413e-01 -8.30502485164628e-02 + 4.14220450790071e-01 -8.54779875163164e-02 + 3.98099898802043e-01 -8.75003551684143e-02 + 3.82361417152145e-01 -8.91539118487549e-02 + 3.67012812949938e-01 -9.04577352136744e-02 + 3.52059448954428e-01 -9.14125244130858e-02 + 3.37508402620579e-01 -9.20698975569944e-02 + 3.23362484181096e-01 -9.24370482908363e-02 + 3.09624084367261e-01 -9.24697923842373e-02 + 2.96293755468272e-01 -9.23622670606858e-02 + 2.83370903129312e-01 -9.19897555434183e-02 + 2.70853535031793e-01 -9.14126750133591e-02 + 2.58737816915769e-01 -9.06671135148306e-02 + 2.47019052739988e-01 -8.97729432930204e-02 + 2.35693903527246e-01 -8.87274220986881e-02 + 2.24755521592725e-01 -8.75580418688866e-02 + 2.14196793622914e-01 -8.62833003191494e-02 + 2.04011333955405e-01 -8.49112533908159e-02 + 1.94192837298268e-01 -8.34452969779509e-02 + 1.84734159226918e-01 -8.18934025781127e-02 + 1.75626054456646e-01 -8.02758698487786e-02 + 1.66858918288587e-01 -7.86084496737449e-02 + 1.58426290110471e-01 -7.68895418961286e-02 + 1.50319200159812e-01 -7.51270351688627e-02 + 1.42526128875168e-01 -7.33413608576655e-02 + 1.35038180671969e-01 -7.15388978061903e-02 + 1.27849040687011e-01 -6.97156113201790e-02 + 1.20948527760174e-01 -6.78811403433585e-02 + 1.14327485726520e-01 -6.60418021962953e-02 + 1.07979453337408e-01 -6.41934386967372e-02 + 1.01894552002694e-01 -6.23456843683916e-02 + 9.60638804275308e-02 -6.05029662954196e-02 + 9.04788853236919e-02 -5.86685553793366e-02 + 8.51312964604805e-02 -5.68450270554785e-02 + 8.00139177362996e-02 -5.50331392699712e-02 + 7.51182333677251e-02 -5.32366201153170e-02 + 7.04360799396603e-02 -5.14581517700259e-02 + 6.59596102739365e-02 -4.96999221177560e-02 + 6.16809021391528e-02 -4.79652498980933e-02 + 5.75939553533738e-02 -4.62523224159701e-02 + 5.36927994773425e-02 -4.45595092963015e-02 + 4.99721163171827e-02 -4.28844263337983e-02 + 4.64252087767243e-02 -4.12292511300908e-02 + 4.30449330853367e-02 -3.95960611215206e-02 + 3.98247762561857e-02 -3.79859513726024e-02 + 3.67604251934450e-02 -3.63964310185422e-02 + 3.38455506187726e-02 -3.48295489141875e-02 + 3.10746565338045e-02 -3.32852832714888e-02 + 2.84426522729682e-02 -3.17631309877224e-02 + 2.59479462715313e-02 -3.02581097804500e-02 + 2.35806727258491e-02 -2.87783720898960e-02 + 2.13379586193463e-02 -2.73212926691211e-02 + 1.92197591809738e-02 -2.58794609330894e-02 + 1.72250219390216e-02 -2.44500206527471e-02 + 1.53362461148815e-02 -2.30507319172916e-02 + 1.35546465191771e-02 -2.16754212282863e-02 + 1.18891791905238e-02 -2.03070715945921e-02 + 1.03502939408908e-02 -1.89320620321851e-02 + 8.91130605466057e-03 -1.75783863139938e-02 + 7.53813877740335e-03 -1.62767162061906e-02 + 6.25261631407701e-03 -1.50030050459626e-02 + 5.11279434609420e-03 -1.36984926934841e-02 + 4.13351214596566e-03 -1.23586032117553e-02 + 3.29319124926354e-03 -1.10101245850993e-02 + 2.61550555648146e-03 -9.65116862965519e-03 + 2.09002183330755e-03 -8.29851601144447e-03 + 1.70078951843963e-03 -6.96281267583815e-03 + 1.36265166348109e-03 -5.67431295008859e-03 + 1.05977091812036e-03 -4.43783511622449e-03 + 7.76752295586629e-04 -3.25343117981278e-03 + 5.09088367705372e-04 -2.11971200576328e-03 + 2.51457101720442e-04 -1.03563109330527e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.41152507493868e-04 1.03804336890630e-03 + 4.71263736944646e-04 2.12757058293535e-03 + 6.99943594043346e-04 3.26857529570577e-03 + 9.32193128484313e-04 4.46218636779492e-03 + 1.17467942772895e-03 5.70972413170852e-03 + 1.43994542427533e-03 7.01025996015618e-03 + 1.74875960694718e-03 8.36460325834191e-03 + 2.11951590798279e-03 9.76507908206140e-03 + 2.62509733655399e-03 1.11886220147912e-02 + 3.25196895044496e-03 1.26421758114203e-02 + 3.97465034233274e-03 1.41283885203257e-02 + 4.82125008770289e-03 1.56307580709229e-02 + 5.78681385913657e-03 1.71508606271287e-02 + 6.84636895293181e-03 1.87061547939764e-02 + 7.95385823673404e-03 2.03287827858700e-02 + 9.16427485256001e-03 2.19844474193354e-02 + 1.04866325918796e-02 2.36680181220581e-02 + 1.19246001481561e-02 2.53798825843331e-02 + 1.34664539799032e-02 2.71314307830888e-02 + 1.51151426347581e-02 2.89238440065633e-02 + 1.68814985227616e-02 3.07508671802106e-02 + 1.87764354986689e-02 3.26068686407149e-02 + 2.07945755995919e-02 3.45003481634749e-02 + 2.29433295368296e-02 3.64281722102988e-02 + 2.52292451944009e-02 3.83886558140635e-02 + 2.76584039930501e-02 4.03804022182471e-02 + 3.02279458793868e-02 4.24121923692621e-02 + 3.29474897596453e-02 4.44785420770728e-02 + 3.58241314284824e-02 4.65778377875867e-02 + 3.88615699902796e-02 4.87123968511837e-02 + 4.20676717891717e-02 5.08781772356130e-02 + 4.54487329341993e-02 5.30746242381647e-02 + 4.90117485491485e-02 5.53002611029898e-02 + 5.27645862937288e-02 5.75519273923613e-02 + 5.67093606250863e-02 5.98355421876917e-02 + 6.08542808522407e-02 6.21481464820482e-02 + 6.52077360665248e-02 6.44866424610369e-02 + 6.97777749333136e-02 6.68483047653571e-02 + 7.45725584053168e-02 6.92290421276930e-02 + 7.96003025603602e-02 7.16257099944468e-02 + 8.48692521878683e-02 7.40353559775043e-02 + 9.03877052429679e-02 7.64548116524863e-02 + 9.61655134799091e-02 7.88762011581258e-02 + 1.02207263913494e-01 8.13045515555609e-02 + 1.08520558648419e-01 8.37388705427050e-02 + 1.15116028351370e-01 8.61695316478935e-02 + 1.22007229910574e-01 8.85790359587486e-02 + 1.29199708937344e-01 9.09693898928607e-02 + 1.36707239581636e-01 9.33170443302486e-02 + 1.44532832289765e-01 9.56345442285116e-02 + 1.52680165789989e-01 9.79325041341286e-02 + 1.61161441053045e-01 1.00189166048500e-01 + 1.70007457308521e-01 1.02310587742487e-01 + 1.79190054721449e-01 1.04432905562834e-01 + 1.88737272862309e-01 1.06459673932072e-01 + 1.98658849288637e-01 1.08368456710055e-01 + 2.08959521814780e-01 1.10157093980485e-01 + 2.19641591893373e-01 1.11840420663148e-01 + 2.30708491271435e-01 1.13421765446694e-01 + 2.42179055605765e-01 1.14797531689102e-01 + 2.54054847054779e-01 1.15956061862792e-01 + 2.66335501246618e-01 1.16912330796287e-01 + 2.79022641080626e-01 1.17663923550265e-01 + 2.92117168343597e-01 1.18248653891892e-01 + 3.05622216334775e-01 1.18493312816741e-01 + 3.19537924072257e-01 1.18497489736340e-01 + 3.33860492946775e-01 1.18251006166221e-01 + 3.48588151721234e-01 1.17646648524711e-01 + 3.63721224567419e-01 1.16827356073084e-01 + 3.79254655371093e-01 1.15711829738200e-01 + 3.95185482070027e-01 1.14309376763544e-01 + 4.11511052759619e-01 1.12629630765949e-01 + 4.28236810162283e-01 1.10757309311154e-01 + 4.45341106820901e-01 1.08539918592541e-01 + 4.62837300814829e-01 1.06125215640029e-01 + 4.80703334536459e-01 1.03396855089698e-01 + 4.98947032463024e-01 1.00451779534968e-01 + 5.17571379732328e-01 9.73486814910668e-02 + 5.36548400903477e-01 9.39688774564715e-02 + 5.55881355199664e-01 9.03838060138069e-02 + 5.75562372757084e-01 8.66043381028199e-02 + 5.95577970398358e-01 8.26174413045570e-02 + 6.15918406419707e-01 7.84356567370351e-02 + 6.36571346336407e-01 7.40624490885372e-02 + 6.57538252289466e-01 6.95719746617823e-02 + 6.78805330161313e-01 6.49684751967319e-02 + 7.00356747433778e-01 6.02530296562983e-02 + 7.22190564422178e-01 5.54942107563349e-02 + 7.44281974327413e-01 5.06608414104289e-02 + 7.66628713730443e-01 4.58296525153133e-02 + 7.89212731568401e-01 4.10099912210156e-02 + 8.12018185533069e-01 3.62261968408074e-02 + 8.35028977005283e-01 3.15060199889171e-02 + 8.58219151715056e-01 2.68336443816806e-02 + 8.81569312265979e-01 2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF43_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF43_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF43_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 -3.34644442304210e-02 + 6.14445718488537e-01 -3.88868243087427e-02 + 5.94530941842471e-01 -4.43132611654412e-02 + 5.74970022740498e-01 -4.96643666397068e-02 + 5.55752003197788e-01 -5.48579023094515e-02 + 5.36876404308979e-01 -5.98525300304434e-02 + 5.18342824936104e-01 -6.46102084095419e-02 + 5.00150385563215e-01 -6.90906898681219e-02 + 4.82288445935981e-01 -7.32102556940118e-02 + 4.64755299574327e-01 -7.69174493160327e-02 + 4.47560043916586e-01 -8.02013672216798e-02 + 4.30710873709413e-01 -8.30502485164628e-02 + 4.14220450790071e-01 -8.54779875163164e-02 + 3.98099898802043e-01 -8.75003551684143e-02 + 3.82361417152145e-01 -8.91539118487549e-02 + 3.67012812949938e-01 -9.04577352136744e-02 + 3.52059448954428e-01 -9.14125244130858e-02 + 3.37508402620579e-01 -9.20698975569944e-02 + 3.23362484181096e-01 -9.24370482908363e-02 + 3.09624084367261e-01 -9.24697923842373e-02 + 2.96293755468272e-01 -9.23622670606858e-02 + 2.83370903129312e-01 -9.19897555434183e-02 + 2.70853535031793e-01 -9.14126750133591e-02 + 2.58737816915769e-01 -9.06671135148306e-02 + 2.47019052739988e-01 -8.97729432930204e-02 + 2.35693903527246e-01 -8.87274220986881e-02 + 2.24755521592725e-01 -8.75580418688866e-02 + 2.14196793622914e-01 -8.62833003191494e-02 + 2.04011333955405e-01 -8.49112533908159e-02 + 1.94192837298268e-01 -8.34452969779509e-02 + 1.84734159226918e-01 -8.18934025781127e-02 + 1.75626054456646e-01 -8.02758698487786e-02 + 1.66858918288587e-01 -7.86084496737449e-02 + 1.58426290110471e-01 -7.68895418961286e-02 + 1.50319200159812e-01 -7.51270351688627e-02 + 1.42526128875168e-01 -7.33413608576655e-02 + 1.35038180671969e-01 -7.15388978061903e-02 + 1.27849040687011e-01 -6.97156113201790e-02 + 1.20948527760174e-01 -6.78811403433585e-02 + 1.14327485726520e-01 -6.60418021962953e-02 + 1.07979453337408e-01 -6.41934386967372e-02 + 1.01894552002694e-01 -6.23456843683916e-02 + 9.60638804275308e-02 -6.05029662954196e-02 + 9.04788853236919e-02 -5.86685553793366e-02 + 8.51312964604805e-02 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-2.16754212282863e-02 + 1.18891791905238e-02 -2.03070715945921e-02 + 1.03502939408908e-02 -1.89320620321851e-02 + 8.91130605466057e-03 -1.75783863139938e-02 + 7.53813877740335e-03 -1.62767162061906e-02 + 6.25261631407701e-03 -1.50030050459626e-02 + 5.11279434609420e-03 -1.36984926934841e-02 + 4.13351214596566e-03 -1.23586032117553e-02 + 3.29319124926354e-03 -1.10101245850993e-02 + 2.61550555648146e-03 -9.65116862965519e-03 + 2.09002183330755e-03 -8.29851601144447e-03 + 1.70078951843963e-03 -6.96281267583815e-03 + 1.36265166348109e-03 -5.67431295008859e-03 + 1.05977091812036e-03 -4.43783511622449e-03 + 7.76752295586629e-04 -3.25343117981278e-03 + 5.09088367705372e-04 -2.11971200576328e-03 + 2.51457101720442e-04 -1.03563109330527e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.41152507493868e-04 1.03804336890630e-03 + 4.71263736944646e-04 2.12757058293535e-03 + 6.99943594043346e-04 3.26857529570577e-03 + 9.32193128484313e-04 4.46218636779492e-03 + 1.17467942772895e-03 5.70972413170852e-03 + 1.43994542427533e-03 7.01025996015618e-03 + 1.74875960694718e-03 8.36460325834191e-03 + 2.11951590798279e-03 9.76507908206140e-03 + 2.62509733655399e-03 1.11886220147912e-02 + 3.25196895044496e-03 1.26421758114203e-02 + 3.97465034233274e-03 1.41283885203257e-02 + 4.82125008770289e-03 1.56307580709229e-02 + 5.78681385913657e-03 1.71508606271287e-02 + 6.84636895293181e-03 1.87061547939764e-02 + 7.95385823673404e-03 2.03287827858700e-02 + 9.16427485256001e-03 2.19844474193354e-02 + 1.04866325918796e-02 2.36680181220581e-02 + 1.19246001481561e-02 2.53798825843331e-02 + 1.34664539799032e-02 2.71314307830888e-02 + 1.51151426347581e-02 2.89238440065633e-02 + 1.68814985227616e-02 3.07508671802106e-02 + 1.87764354986689e-02 3.26068686407149e-02 + 2.07945755995919e-02 3.45003481634749e-02 + 2.29433295368296e-02 3.64281722102988e-02 + 2.52292451944009e-02 3.83886558140635e-02 + 2.76584039930501e-02 4.03804022182471e-02 + 3.02279458793868e-02 4.24121923692621e-02 + 3.29474897596453e-02 4.44785420770728e-02 + 3.58241314284824e-02 4.65778377875867e-02 + 3.88615699902796e-02 4.87123968511837e-02 + 4.20676717891717e-02 5.08781772356130e-02 + 4.54487329341993e-02 5.30746242381647e-02 + 4.90117485491485e-02 5.53002611029898e-02 + 5.27645862937288e-02 5.75519273923613e-02 + 5.67093606250863e-02 5.98355421876917e-02 + 6.08542808522407e-02 6.21481464820482e-02 + 6.52077360665248e-02 6.44866424610369e-02 + 6.97777749333136e-02 6.68483047653571e-02 + 7.45725584053168e-02 6.92290421276930e-02 + 7.96003025603602e-02 7.16257099944468e-02 + 8.48692521878683e-02 7.40353559775043e-02 + 9.03877052429679e-02 7.64548116524863e-02 + 9.61655134799091e-02 7.88762011581258e-02 + 1.02207263913494e-01 8.13045515555609e-02 + 1.08520558648419e-01 8.37388705427050e-02 + 1.15116028351370e-01 8.61695316478935e-02 + 1.22007229910574e-01 8.85790359587486e-02 + 1.29199708937344e-01 9.09693898928607e-02 + 1.36707239581636e-01 9.33170443302486e-02 + 1.44532832289765e-01 9.56345442285116e-02 + 1.52680165789989e-01 9.79325041341286e-02 + 1.61161441053045e-01 1.00189166048500e-01 + 1.70007457308521e-01 1.02310587742487e-01 + 1.79190054721449e-01 1.04432905562834e-01 + 1.88737272862309e-01 1.06459673932072e-01 + 1.98658849288637e-01 1.08368456710055e-01 + 2.08959521814780e-01 1.10157093980485e-01 + 2.19641591893373e-01 1.11840420663148e-01 + 2.30708491271435e-01 1.13421765446694e-01 + 2.42179055605765e-01 1.14797531689102e-01 + 2.54054847054779e-01 1.15956061862792e-01 + 2.66335501246618e-01 1.16912330796287e-01 + 2.79022641080626e-01 1.17663923550265e-01 + 2.92117168343597e-01 1.18248653891892e-01 + 3.05622216334775e-01 1.18493312816741e-01 + 3.19537924072257e-01 1.18497489736340e-01 + 3.33860492946775e-01 1.18251006166221e-01 + 3.48588151721234e-01 1.17646648524711e-01 + 3.63721224567419e-01 1.16827356073084e-01 + 3.79254655371093e-01 1.15711829738200e-01 + 3.95185482070027e-01 1.14309376763544e-01 + 4.11511052759619e-01 1.12629630765949e-01 + 4.28236810162283e-01 1.10757309311154e-01 + 4.45341106820901e-01 1.08539918592541e-01 + 4.62837300814829e-01 1.06125215640029e-01 + 4.80703334536459e-01 1.03396855089698e-01 + 4.98947032463024e-01 1.00451779534968e-01 + 5.17571379732328e-01 9.73486814910668e-02 + 5.36548400903477e-01 9.39688774564715e-02 + 5.55881355199664e-01 9.03838060138069e-02 + 5.75562372757084e-01 8.66043381028199e-02 + 5.95577970398358e-01 8.26174413045570e-02 + 6.15918406419707e-01 7.84356567370351e-02 + 6.36571346336407e-01 7.40624490885372e-02 + 6.57538252289466e-01 6.95719746617823e-02 + 6.78805330161313e-01 6.49684751967319e-02 + 7.00356747433778e-01 6.02530296562983e-02 + 7.22190564422178e-01 5.54942107563349e-02 + 7.44281974327413e-01 5.06608414104289e-02 + 7.66628713730443e-01 4.58296525153133e-02 + 7.89212731568401e-01 4.10099912210156e-02 + 8.12018185533069e-01 3.62261968408074e-02 + 8.35028977005283e-01 3.15060199889171e-02 + 8.58219151715056e-01 2.68336443816806e-02 + 8.81569312265979e-01 2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF44_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF44_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF44_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 -3.34644442304210e-02 + 6.14445718488537e-01 -3.88868243087427e-02 + 5.94530941842471e-01 -4.43132611654412e-02 + 5.74970022740498e-01 -4.96643666397068e-02 + 5.55752003197788e-01 -5.48579023094515e-02 + 5.36876404308979e-01 -5.98525300304434e-02 + 5.18342824936104e-01 -6.46102084095419e-02 + 5.00150385563215e-01 -6.90906898681219e-02 + 4.82288445935981e-01 -7.32102556940118e-02 + 4.64755299574327e-01 -7.69174493160327e-02 + 4.47560043916586e-01 -8.02013672216798e-02 + 4.30710873709413e-01 -8.30502485164628e-02 + 4.14220450790071e-01 -8.54779875163164e-02 + 3.98099898802043e-01 -8.75003551684143e-02 + 3.82361417152145e-01 -8.91539118487549e-02 + 3.67012812949938e-01 -9.04577352136744e-02 + 3.52059448954428e-01 -9.14125244130858e-02 + 3.37508402620579e-01 -9.20698975569944e-02 + 3.23362484181096e-01 -9.24370482908363e-02 + 3.09624084367261e-01 -9.24697923842373e-02 + 2.96293755468272e-01 -9.23622670606858e-02 + 2.83370903129312e-01 -9.19897555434183e-02 + 2.70853535031793e-01 -9.14126750133591e-02 + 2.58737816915769e-01 -9.06671135148306e-02 + 2.47019052739988e-01 -8.97729432930204e-02 + 2.35693903527246e-01 -8.87274220986881e-02 + 2.24755521592725e-01 -8.75580418688866e-02 + 2.14196793622914e-01 -8.62833003191494e-02 + 2.04011333955405e-01 -8.49112533908159e-02 + 1.94192837298268e-01 -8.34452969779509e-02 + 1.84734159226918e-01 -8.18934025781127e-02 + 1.75626054456646e-01 -8.02758698487786e-02 + 1.66858918288587e-01 -7.86084496737449e-02 + 1.58426290110471e-01 -7.68895418961286e-02 + 1.50319200159812e-01 -7.51270351688627e-02 + 1.42526128875168e-01 -7.33413608576655e-02 + 1.35038180671969e-01 -7.15388978061903e-02 + 1.27849040687011e-01 -6.97156113201790e-02 + 1.20948527760174e-01 -6.78811403433585e-02 + 1.14327485726520e-01 -6.60418021962953e-02 + 1.07979453337408e-01 -6.41934386967372e-02 + 1.01894552002694e-01 -6.23456843683916e-02 + 9.60638804275308e-02 -6.05029662954196e-02 + 9.04788853236919e-02 -5.86685553793366e-02 + 8.51312964604805e-02 -5.68450270554785e-02 + 8.00139177362996e-02 -5.50331392699712e-02 + 7.51182333677251e-02 -5.32366201153170e-02 + 7.04360799396603e-02 -5.14581517700259e-02 + 6.59596102739365e-02 -4.96999221177560e-02 + 6.16809021391528e-02 -4.79652498980933e-02 + 5.75939553533738e-02 -4.62523224159701e-02 + 5.36927994773425e-02 -4.45595092963015e-02 + 4.99721163171827e-02 -4.28844263337983e-02 + 4.64252087767243e-02 -4.12292511300908e-02 + 4.30449330853367e-02 -3.95960611215206e-02 + 3.98247762561857e-02 -3.79859513726024e-02 + 3.67604251934450e-02 -3.63964310185422e-02 + 3.38455506187726e-02 -3.48295489141875e-02 + 3.10746565338045e-02 -3.32852832714888e-02 + 2.84426522729682e-02 -3.17631309877224e-02 + 2.59479462715313e-02 -3.02581097804500e-02 + 2.35806727258491e-02 -2.87783720898960e-02 + 2.13379586193463e-02 -2.73212926691211e-02 + 1.92197591809738e-02 -2.58794609330894e-02 + 1.72250219390216e-02 -2.44500206527471e-02 + 1.53362461148815e-02 -2.30507319172916e-02 + 1.35546465191771e-02 -2.16754212282863e-02 + 1.18891791905238e-02 -2.03070715945921e-02 + 1.03502939408908e-02 -1.89320620321851e-02 + 8.91130605466057e-03 -1.75783863139938e-02 + 7.53813877740335e-03 -1.62767162061906e-02 + 6.25261631407701e-03 -1.50030050459626e-02 + 5.11279434609420e-03 -1.36984926934841e-02 + 4.13351214596566e-03 -1.23586032117553e-02 + 3.29319124926354e-03 -1.10101245850993e-02 + 2.61550555648146e-03 -9.65116862965519e-03 + 2.09002183330755e-03 -8.29851601144447e-03 + 1.70078951843963e-03 -6.96281267583815e-03 + 1.36265166348109e-03 -5.67431295008859e-03 + 1.05977091812036e-03 -4.43783511622449e-03 + 7.76752295586629e-04 -3.25343117981278e-03 + 5.09088367705372e-04 -2.11971200576328e-03 + 2.51457101720442e-04 -1.03563109330527e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.41152507493868e-04 1.03804336890630e-03 + 4.71263736944646e-04 2.12757058293535e-03 + 6.99943594043346e-04 3.26857529570577e-03 + 9.32193128484313e-04 4.46218636779492e-03 + 1.17467942772895e-03 5.70972413170852e-03 + 1.43994542427533e-03 7.01025996015618e-03 + 1.74875960694718e-03 8.36460325834191e-03 + 2.11951590798279e-03 9.76507908206140e-03 + 2.62509733655399e-03 1.11886220147912e-02 + 3.25196895044496e-03 1.26421758114203e-02 + 3.97465034233274e-03 1.41283885203257e-02 + 4.82125008770289e-03 1.56307580709229e-02 + 5.78681385913657e-03 1.71508606271287e-02 + 6.84636895293181e-03 1.87061547939764e-02 + 7.95385823673404e-03 2.03287827858700e-02 + 9.16427485256001e-03 2.19844474193354e-02 + 1.04866325918796e-02 2.36680181220581e-02 + 1.19246001481561e-02 2.53798825843331e-02 + 1.34664539799032e-02 2.71314307830888e-02 + 1.51151426347581e-02 2.89238440065633e-02 + 1.68814985227616e-02 3.07508671802106e-02 + 1.87764354986689e-02 3.26068686407149e-02 + 2.07945755995919e-02 3.45003481634749e-02 + 2.29433295368296e-02 3.64281722102988e-02 + 2.52292451944009e-02 3.83886558140635e-02 + 2.76584039930501e-02 4.03804022182471e-02 + 3.02279458793868e-02 4.24121923692621e-02 + 3.29474897596453e-02 4.44785420770728e-02 + 3.58241314284824e-02 4.65778377875867e-02 + 3.88615699902796e-02 4.87123968511837e-02 + 4.20676717891717e-02 5.08781772356130e-02 + 4.54487329341993e-02 5.30746242381647e-02 + 4.90117485491485e-02 5.53002611029898e-02 + 5.27645862937288e-02 5.75519273923613e-02 + 5.67093606250863e-02 5.98355421876917e-02 + 6.08542808522407e-02 6.21481464820482e-02 + 6.52077360665248e-02 6.44866424610369e-02 + 6.97777749333136e-02 6.68483047653571e-02 + 7.45725584053168e-02 6.92290421276930e-02 + 7.96003025603602e-02 7.16257099944468e-02 + 8.48692521878683e-02 7.40353559775043e-02 + 9.03877052429679e-02 7.64548116524863e-02 + 9.61655134799091e-02 7.88762011581258e-02 + 1.02207263913494e-01 8.13045515555609e-02 + 1.08520558648419e-01 8.37388705427050e-02 + 1.15116028351370e-01 8.61695316478935e-02 + 1.22007229910574e-01 8.85790359587486e-02 + 1.29199708937344e-01 9.09693898928607e-02 + 1.36707239581636e-01 9.33170443302486e-02 + 1.44532832289765e-01 9.56345442285116e-02 + 1.52680165789989e-01 9.79325041341286e-02 + 1.61161441053045e-01 1.00189166048500e-01 + 1.70007457308521e-01 1.02310587742487e-01 + 1.79190054721449e-01 1.04432905562834e-01 + 1.88737272862309e-01 1.06459673932072e-01 + 1.98658849288637e-01 1.08368456710055e-01 + 2.08959521814780e-01 1.10157093980485e-01 + 2.19641591893373e-01 1.11840420663148e-01 + 2.30708491271435e-01 1.13421765446694e-01 + 2.42179055605765e-01 1.14797531689102e-01 + 2.54054847054779e-01 1.15956061862792e-01 + 2.66335501246618e-01 1.16912330796287e-01 + 2.79022641080626e-01 1.17663923550265e-01 + 2.92117168343597e-01 1.18248653891892e-01 + 3.05622216334775e-01 1.18493312816741e-01 + 3.19537924072257e-01 1.18497489736340e-01 + 3.33860492946775e-01 1.18251006166221e-01 + 3.48588151721234e-01 1.17646648524711e-01 + 3.63721224567419e-01 1.16827356073084e-01 + 3.79254655371093e-01 1.15711829738200e-01 + 3.95185482070027e-01 1.14309376763544e-01 + 4.11511052759619e-01 1.12629630765949e-01 + 4.28236810162283e-01 1.10757309311154e-01 + 4.45341106820901e-01 1.08539918592541e-01 + 4.62837300814829e-01 1.06125215640029e-01 + 4.80703334536459e-01 1.03396855089698e-01 + 4.98947032463024e-01 1.00451779534968e-01 + 5.17571379732328e-01 9.73486814910668e-02 + 5.36548400903477e-01 9.39688774564715e-02 + 5.55881355199664e-01 9.03838060138069e-02 + 5.75562372757084e-01 8.66043381028199e-02 + 5.95577970398358e-01 8.26174413045570e-02 + 6.15918406419707e-01 7.84356567370351e-02 + 6.36571346336407e-01 7.40624490885372e-02 + 6.57538252289466e-01 6.95719746617823e-02 + 6.78805330161313e-01 6.49684751967319e-02 + 7.00356747433778e-01 6.02530296562983e-02 + 7.22190564422178e-01 5.54942107563349e-02 + 7.44281974327413e-01 5.06608414104289e-02 + 7.66628713730443e-01 4.58296525153133e-02 + 7.89212731568401e-01 4.10099912210156e-02 + 8.12018185533069e-01 3.62261968408074e-02 + 8.35028977005283e-01 3.15060199889171e-02 + 8.58219151715056e-01 2.68336443816806e-02 + 8.81569312265979e-01 2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF45_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF45_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF45_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 -3.34644442304210e-02 + 6.14445718488537e-01 -3.88868243087427e-02 + 5.94530941842471e-01 -4.43132611654412e-02 + 5.74970022740498e-01 -4.96643666397068e-02 + 5.55752003197788e-01 -5.48579023094515e-02 + 5.36876404308979e-01 -5.98525300304434e-02 + 5.18342824936104e-01 -6.46102084095419e-02 + 5.00150385563215e-01 -6.90906898681219e-02 + 4.82288445935981e-01 -7.32102556940118e-02 + 4.64755299574327e-01 -7.69174493160327e-02 + 4.47560043916586e-01 -8.02013672216798e-02 + 4.30710873709413e-01 -8.30502485164628e-02 + 4.14220450790071e-01 -8.54779875163164e-02 + 3.98099898802043e-01 -8.75003551684143e-02 + 3.82361417152145e-01 -8.91539118487549e-02 + 3.67012812949938e-01 -9.04577352136744e-02 + 3.52059448954428e-01 -9.14125244130858e-02 + 3.37508402620579e-01 -9.20698975569944e-02 + 3.23362484181096e-01 -9.24370482908363e-02 + 3.09624084367261e-01 -9.24697923842373e-02 + 2.96293755468272e-01 -9.23622670606858e-02 + 2.83370903129312e-01 -9.19897555434183e-02 + 2.70853535031793e-01 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-2.16754212282863e-02 + 1.18891791905238e-02 -2.03070715945921e-02 + 1.03502939408908e-02 -1.89320620321851e-02 + 8.91130605466057e-03 -1.75783863139938e-02 + 7.53813877740335e-03 -1.62767162061906e-02 + 6.25261631407701e-03 -1.50030050459626e-02 + 5.11279434609420e-03 -1.36984926934841e-02 + 4.13351214596566e-03 -1.23586032117553e-02 + 3.29319124926354e-03 -1.10101245850993e-02 + 2.61550555648146e-03 -9.65116862965519e-03 + 2.09002183330755e-03 -8.29851601144447e-03 + 1.70078951843963e-03 -6.96281267583815e-03 + 1.36265166348109e-03 -5.67431295008859e-03 + 1.05977091812036e-03 -4.43783511622449e-03 + 7.76752295586629e-04 -3.25343117981278e-03 + 5.09088367705372e-04 -2.11971200576328e-03 + 2.51457101720442e-04 -1.03563109330527e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.41152507493868e-04 1.03804336890630e-03 + 4.71263736944646e-04 2.12757058293535e-03 + 6.99943594043346e-04 3.26857529570577e-03 + 9.32193128484313e-04 4.46218636779492e-03 + 1.17467942772895e-03 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3.29474897596453e-02 4.44785420770728e-02 + 3.58241314284824e-02 4.65778377875867e-02 + 3.88615699902796e-02 4.87123968511837e-02 + 4.20676717891717e-02 5.08781772356130e-02 + 4.54487329341993e-02 5.30746242381647e-02 + 4.90117485491485e-02 5.53002611029898e-02 + 5.27645862937288e-02 5.75519273923613e-02 + 5.67093606250863e-02 5.98355421876917e-02 + 6.08542808522407e-02 6.21481464820482e-02 + 6.52077360665248e-02 6.44866424610369e-02 + 6.97777749333136e-02 6.68483047653571e-02 + 7.45725584053168e-02 6.92290421276930e-02 + 7.96003025603602e-02 7.16257099944468e-02 + 8.48692521878683e-02 7.40353559775043e-02 + 9.03877052429679e-02 7.64548116524863e-02 + 9.61655134799091e-02 7.88762011581258e-02 + 1.02207263913494e-01 8.13045515555609e-02 + 1.08520558648419e-01 8.37388705427050e-02 + 1.15116028351370e-01 8.61695316478935e-02 + 1.22007229910574e-01 8.85790359587486e-02 + 1.29199708937344e-01 9.09693898928607e-02 + 1.36707239581636e-01 9.33170443302486e-02 + 1.44532832289765e-01 9.56345442285116e-02 + 1.52680165789989e-01 9.79325041341286e-02 + 1.61161441053045e-01 1.00189166048500e-01 + 1.70007457308521e-01 1.02310587742487e-01 + 1.79190054721449e-01 1.04432905562834e-01 + 1.88737272862309e-01 1.06459673932072e-01 + 1.98658849288637e-01 1.08368456710055e-01 + 2.08959521814780e-01 1.10157093980485e-01 + 2.19641591893373e-01 1.11840420663148e-01 + 2.30708491271435e-01 1.13421765446694e-01 + 2.42179055605765e-01 1.14797531689102e-01 + 2.54054847054779e-01 1.15956061862792e-01 + 2.66335501246618e-01 1.16912330796287e-01 + 2.79022641080626e-01 1.17663923550265e-01 + 2.92117168343597e-01 1.18248653891892e-01 + 3.05622216334775e-01 1.18493312816741e-01 + 3.19537924072257e-01 1.18497489736340e-01 + 3.33860492946775e-01 1.18251006166221e-01 + 3.48588151721234e-01 1.17646648524711e-01 + 3.63721224567419e-01 1.16827356073084e-01 + 3.79254655371093e-01 1.15711829738200e-01 + 3.95185482070027e-01 1.14309376763544e-01 + 4.11511052759619e-01 1.12629630765949e-01 + 4.28236810162283e-01 1.10757309311154e-01 + 4.45341106820901e-01 1.08539918592541e-01 + 4.62837300814829e-01 1.06125215640029e-01 + 4.80703334536459e-01 1.03396855089698e-01 + 4.98947032463024e-01 1.00451779534968e-01 + 5.17571379732328e-01 9.73486814910668e-02 + 5.36548400903477e-01 9.39688774564715e-02 + 5.55881355199664e-01 9.03838060138069e-02 + 5.75562372757084e-01 8.66043381028199e-02 + 5.95577970398358e-01 8.26174413045570e-02 + 6.15918406419707e-01 7.84356567370351e-02 + 6.36571346336407e-01 7.40624490885372e-02 + 6.57538252289466e-01 6.95719746617823e-02 + 6.78805330161313e-01 6.49684751967319e-02 + 7.00356747433778e-01 6.02530296562983e-02 + 7.22190564422178e-01 5.54942107563349e-02 + 7.44281974327413e-01 5.06608414104289e-02 + 7.66628713730443e-01 4.58296525153133e-02 + 7.89212731568401e-01 4.10099912210156e-02 + 8.12018185533069e-01 3.62261968408074e-02 + 8.35028977005283e-01 3.15060199889171e-02 + 8.58219151715056e-01 2.68336443816806e-02 + 8.81569312265979e-01 2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF46_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF46_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF46_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 -3.34644442304210e-02 + 6.14445718488537e-01 -3.88868243087427e-02 + 5.94530941842471e-01 -4.43132611654412e-02 + 5.74970022740498e-01 -4.96643666397068e-02 + 5.55752003197788e-01 -5.48579023094515e-02 + 5.36876404308979e-01 -5.98525300304434e-02 + 5.18342824936104e-01 -6.46102084095419e-02 + 5.00150385563215e-01 -6.90906898681219e-02 + 4.82288445935981e-01 -7.32102556940118e-02 + 4.64755299574327e-01 -7.69174493160327e-02 + 4.47560043916586e-01 -8.02013672216798e-02 + 4.30710873709413e-01 -8.30502485164628e-02 + 4.14220450790071e-01 -8.54779875163164e-02 + 3.98099898802043e-01 -8.75003551684143e-02 + 3.82361417152145e-01 -8.91539118487549e-02 + 3.67012812949938e-01 -9.04577352136744e-02 + 3.52059448954428e-01 -9.14125244130858e-02 + 3.37508402620579e-01 -9.20698975569944e-02 + 3.23362484181096e-01 -9.24370482908363e-02 + 3.09624084367261e-01 -9.24697923842373e-02 + 2.96293755468272e-01 -9.23622670606858e-02 + 2.83370903129312e-01 -9.19897555434183e-02 + 2.70853535031793e-01 -9.14126750133591e-02 + 2.58737816915769e-01 -9.06671135148306e-02 + 2.47019052739988e-01 -8.97729432930204e-02 + 2.35693903527246e-01 -8.87274220986881e-02 + 2.24755521592725e-01 -8.75580418688866e-02 + 2.14196793622914e-01 -8.62833003191494e-02 + 2.04011333955405e-01 -8.49112533908159e-02 + 1.94192837298268e-01 -8.34452969779509e-02 + 1.84734159226918e-01 -8.18934025781127e-02 + 1.75626054456646e-01 -8.02758698487786e-02 + 1.66858918288587e-01 -7.86084496737449e-02 + 1.58426290110471e-01 -7.68895418961286e-02 + 1.50319200159812e-01 -7.51270351688627e-02 + 1.42526128875168e-01 -7.33413608576655e-02 + 1.35038180671969e-01 -7.15388978061903e-02 + 1.27849040687011e-01 -6.97156113201790e-02 + 1.20948527760174e-01 -6.78811403433585e-02 + 1.14327485726520e-01 -6.60418021962953e-02 + 1.07979453337408e-01 -6.41934386967372e-02 + 1.01894552002694e-01 -6.23456843683916e-02 + 9.60638804275308e-02 -6.05029662954196e-02 + 9.04788853236919e-02 -5.86685553793366e-02 + 8.51312964604805e-02 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2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF47_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF47_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF47_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 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2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF48_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF48_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF48_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 -3.34644442304210e-02 + 6.14445718488537e-01 -3.88868243087427e-02 + 5.94530941842471e-01 -4.43132611654412e-02 + 5.74970022740498e-01 -4.96643666397068e-02 + 5.55752003197788e-01 -5.48579023094515e-02 + 5.36876404308979e-01 -5.98525300304434e-02 + 5.18342824936104e-01 -6.46102084095419e-02 + 5.00150385563215e-01 -6.90906898681219e-02 + 4.82288445935981e-01 -7.32102556940118e-02 + 4.64755299574327e-01 -7.69174493160327e-02 + 4.47560043916586e-01 -8.02013672216798e-02 + 4.30710873709413e-01 -8.30502485164628e-02 + 4.14220450790071e-01 -8.54779875163164e-02 + 3.98099898802043e-01 -8.75003551684143e-02 + 3.82361417152145e-01 -8.91539118487549e-02 + 3.67012812949938e-01 -9.04577352136744e-02 + 3.52059448954428e-01 -9.14125244130858e-02 + 3.37508402620579e-01 -9.20698975569944e-02 + 3.23362484181096e-01 -9.24370482908363e-02 + 3.09624084367261e-01 -9.24697923842373e-02 + 2.96293755468272e-01 -9.23622670606858e-02 + 2.83370903129312e-01 -9.19897555434183e-02 + 2.70853535031793e-01 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-2.16754212282863e-02 + 1.18891791905238e-02 -2.03070715945921e-02 + 1.03502939408908e-02 -1.89320620321851e-02 + 8.91130605466057e-03 -1.75783863139938e-02 + 7.53813877740335e-03 -1.62767162061906e-02 + 6.25261631407701e-03 -1.50030050459626e-02 + 5.11279434609420e-03 -1.36984926934841e-02 + 4.13351214596566e-03 -1.23586032117553e-02 + 3.29319124926354e-03 -1.10101245850993e-02 + 2.61550555648146e-03 -9.65116862965519e-03 + 2.09002183330755e-03 -8.29851601144447e-03 + 1.70078951843963e-03 -6.96281267583815e-03 + 1.36265166348109e-03 -5.67431295008859e-03 + 1.05977091812036e-03 -4.43783511622449e-03 + 7.76752295586629e-04 -3.25343117981278e-03 + 5.09088367705372e-04 -2.11971200576328e-03 + 2.51457101720442e-04 -1.03563109330527e-03 + 0.00000000000000e+00 0.00000000000000e+00 + 2.41152507493868e-04 1.03804336890630e-03 + 4.71263736944646e-04 2.12757058293535e-03 + 6.99943594043346e-04 3.26857529570577e-03 + 9.32193128484313e-04 4.46218636779492e-03 + 1.17467942772895e-03 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3.29474897596453e-02 4.44785420770728e-02 + 3.58241314284824e-02 4.65778377875867e-02 + 3.88615699902796e-02 4.87123968511837e-02 + 4.20676717891717e-02 5.08781772356130e-02 + 4.54487329341993e-02 5.30746242381647e-02 + 4.90117485491485e-02 5.53002611029898e-02 + 5.27645862937288e-02 5.75519273923613e-02 + 5.67093606250863e-02 5.98355421876917e-02 + 6.08542808522407e-02 6.21481464820482e-02 + 6.52077360665248e-02 6.44866424610369e-02 + 6.97777749333136e-02 6.68483047653571e-02 + 7.45725584053168e-02 6.92290421276930e-02 + 7.96003025603602e-02 7.16257099944468e-02 + 8.48692521878683e-02 7.40353559775043e-02 + 9.03877052429679e-02 7.64548116524863e-02 + 9.61655134799091e-02 7.88762011581258e-02 + 1.02207263913494e-01 8.13045515555609e-02 + 1.08520558648419e-01 8.37388705427050e-02 + 1.15116028351370e-01 8.61695316478935e-02 + 1.22007229910574e-01 8.85790359587486e-02 + 1.29199708937344e-01 9.09693898928607e-02 + 1.36707239581636e-01 9.33170443302486e-02 + 1.44532832289765e-01 9.56345442285116e-02 + 1.52680165789989e-01 9.79325041341286e-02 + 1.61161441053045e-01 1.00189166048500e-01 + 1.70007457308521e-01 1.02310587742487e-01 + 1.79190054721449e-01 1.04432905562834e-01 + 1.88737272862309e-01 1.06459673932072e-01 + 1.98658849288637e-01 1.08368456710055e-01 + 2.08959521814780e-01 1.10157093980485e-01 + 2.19641591893373e-01 1.11840420663148e-01 + 2.30708491271435e-01 1.13421765446694e-01 + 2.42179055605765e-01 1.14797531689102e-01 + 2.54054847054779e-01 1.15956061862792e-01 + 2.66335501246618e-01 1.16912330796287e-01 + 2.79022641080626e-01 1.17663923550265e-01 + 2.92117168343597e-01 1.18248653891892e-01 + 3.05622216334775e-01 1.18493312816741e-01 + 3.19537924072257e-01 1.18497489736340e-01 + 3.33860492946775e-01 1.18251006166221e-01 + 3.48588151721234e-01 1.17646648524711e-01 + 3.63721224567419e-01 1.16827356073084e-01 + 3.79254655371093e-01 1.15711829738200e-01 + 3.95185482070027e-01 1.14309376763544e-01 + 4.11511052759619e-01 1.12629630765949e-01 + 4.28236810162283e-01 1.10757309311154e-01 + 4.45341106820901e-01 1.08539918592541e-01 + 4.62837300814829e-01 1.06125215640029e-01 + 4.80703334536459e-01 1.03396855089698e-01 + 4.98947032463024e-01 1.00451779534968e-01 + 5.17571379732328e-01 9.73486814910668e-02 + 5.36548400903477e-01 9.39688774564715e-02 + 5.55881355199664e-01 9.03838060138069e-02 + 5.75562372757084e-01 8.66043381028199e-02 + 5.95577970398358e-01 8.26174413045570e-02 + 6.15918406419707e-01 7.84356567370351e-02 + 6.36571346336407e-01 7.40624490885372e-02 + 6.57538252289466e-01 6.95719746617823e-02 + 6.78805330161313e-01 6.49684751967319e-02 + 7.00356747433778e-01 6.02530296562983e-02 + 7.22190564422178e-01 5.54942107563349e-02 + 7.44281974327413e-01 5.06608414104289e-02 + 7.66628713730443e-01 4.58296525153133e-02 + 7.89212731568401e-01 4.10099912210156e-02 + 8.12018185533069e-01 3.62261968408074e-02 + 8.35028977005283e-01 3.15060199889171e-02 + 8.58219151715056e-01 2.68336443816806e-02 + 8.81569312265979e-01 2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF49_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF49_Coords.txt new file mode 100644 index 00000000..179c7b8f --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AF49_Coords.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.250000 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 -3.71663624309444e-04 + 9.76017568294686e-01 2.09740027382490e-03 + 9.52031329328083e-01 3.99388322551278e-03 + 9.28070638676756e-01 5.29329818508414e-03 + 9.04146732423838e-01 6.03552788264997e-03 + 8.80309441682373e-01 5.94483425110475e-03 + 8.56610087823544e-01 5.07205375524694e-03 + 8.33094779308812e-01 3.48518207679764e-03 + 8.09801500212952e-01 1.24198889436214e-03 + 7.86768732939441e-01 -1.61714401887065e-03 + 7.64029448545206e-01 -5.05415831433425e-03 + 7.41600306402727e-01 -8.95103649024531e-03 + 7.19505313316081e-01 -1.32664966742413e-02 + 6.97760620781954e-01 -1.79392345429141e-02 + 6.76379522029838e-01 -2.29138874387622e-02 + 6.55367086965139e-01 -2.81158064050698e-02 + 6.34723160292757e-01 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4.28236810162283e-01 1.10757309311154e-01 + 4.45341106820901e-01 1.08539918592541e-01 + 4.62837300814829e-01 1.06125215640029e-01 + 4.80703334536459e-01 1.03396855089698e-01 + 4.98947032463024e-01 1.00451779534968e-01 + 5.17571379732328e-01 9.73486814910668e-02 + 5.36548400903477e-01 9.39688774564715e-02 + 5.55881355199664e-01 9.03838060138069e-02 + 5.75562372757084e-01 8.66043381028199e-02 + 5.95577970398358e-01 8.26174413045570e-02 + 6.15918406419707e-01 7.84356567370351e-02 + 6.36571346336407e-01 7.40624490885372e-02 + 6.57538252289466e-01 6.95719746617823e-02 + 6.78805330161313e-01 6.49684751967319e-02 + 7.00356747433778e-01 6.02530296562983e-02 + 7.22190564422178e-01 5.54942107563349e-02 + 7.44281974327413e-01 5.06608414104289e-02 + 7.66628713730443e-01 4.58296525153133e-02 + 7.89212731568401e-01 4.10099912210156e-02 + 8.12018185533069e-01 3.62261968408074e-02 + 8.35028977005283e-01 3.15060199889171e-02 + 8.58219151715056e-01 2.68336443816806e-02 + 8.81569312265979e-01 2.22287377219739e-02 + 9.05060689011999e-01 1.77175246606552e-02 + 9.28671627335113e-01 1.33156680593407e-02 + 9.52381403156938e-01 9.07315533594737e-03 + 9.76165312677752e-01 4.93304948753480e-03 + 1.00000000000000e+00 9.38336381193382e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00.dat index 8c1fee1d..4cd74ebb 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00.dat @@ -5,170 +5,216 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_00_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF00_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF00_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting -True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ - -28.000000 alpha0 ! 0-lift angle of attack, depends on airfoil. - 0.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -0.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - 0.000000 Cn2 ! As Cn1 for negative AOAs. -Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.350000 Cd0 ! 2D drag coefficient value at 0-lift. - -0.000100 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 9.99999999999994e-05 3.50000000000000e-01 -1.00000000000000e-04 --1.77714285740401e+02 1.00000000000003e-04 3.50000000000000e-01 -1.00000000000003e-04 --1.75428571400002e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.73142857116900e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.70857160423602e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.68571631778825e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.66285714267592e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.63999999984490e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.61714472886699e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.59428371284127e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.57142842639350e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.54857313994574e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.52571428568978e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.50285714285875e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.48000000002773e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.43857142836002e+02 1.00000000000044e-04 3.50000000000000e-01 -9.99999999999890e-05 --1.39714285726526e+02 1.00000000000044e-04 3.50000000000000e-01 -9.99999999999890e-05 --1.35571428559755e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.31428571450280e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.27285714283509e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.23142857116737e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.19000000007262e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.14857142840491e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.10714285731016e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.06571428564245e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.02428571454769e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --9.82857142879980e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --9.41428571212269e+01 1.00000000000003e-04 3.50000000000000e-01 -9.99999999999890e-05 --9.00000000117516e+01 1.00000000000000e-04 3.50000000000000e-01 -9.99999999999890e-05 --8.58571428449804e+01 1.00000000000003e-04 3.50000000000000e-01 -9.99999999999890e-05 --8.17142857355051e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --7.75714285687340e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --7.34285714019628e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --6.92857142924875e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 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+ 1.30303030303030e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.36363636363636e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.42424242424242e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.48484848484848e+01 9.99999999997669e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.54545454545455e+01 1.00000000000211e-04 3.50000000000000e-01 -1.00000000000003e-04 + 1.60606060606061e+01 9.99999999997669e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.66666666666667e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.72727272727273e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.78787878787879e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.84848484848485e+01 9.99999999997669e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.90909090909091e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.96969696969697e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 2.03030303030303e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 2.09090909090909e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 2.15151515151515e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 2.21212121212121e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 2.27272727272727e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 2.33333333333333e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 2.39393939393939e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 2.45454545454545e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 2.51515151515151e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 2.57575757575758e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 2.63636363636364e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 2.69696969696970e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 2.75757575757576e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 2.81818181818182e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 2.87878787878788e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 2.93939393939394e+01 1.00000000000211e-04 3.50000000000000e-01 -9.99999999999890e-05 + 3.00000000000000e+01 9.99999999998780e-05 3.50000000000000e-01 -9.99999999999890e-05 + 3.30000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 3.60000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 3.90000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 4.20000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 4.50000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 4.80000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 5.10000000000000e+01 1.00000000000044e-04 3.50000000000000e-01 -9.99999999999890e-05 + 5.40000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 5.70000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 6.00000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 6.30000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 6.60000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 6.90000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 7.20000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 7.50000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 7.80000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 8.10000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 8.40000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 8.70000000000000e+01 1.00000000000003e-04 3.50000000000000e-01 -9.99999999999890e-05 + 9.00000000000000e+01 1.00000000000000e-04 3.50000000000000e-01 -9.99999999999890e-05 + 9.30000000000000e+01 1.00000000000003e-04 3.50000000000000e-01 -9.99999999999890e-05 + 9.60000000000000e+01 1.00000000000003e-04 3.50000000000000e-01 -9.99999999999890e-05 + 9.90000000000000e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.02000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.05000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.08000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.11000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.14000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.17000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.20000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.23000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.26000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.29000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.32000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.35000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.38000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.41000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.44000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.47000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.50000000000000e+02 1.00000000000100e-04 3.50000000000000e-01 -9.99999999999890e-05 + 1.53000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.56000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.59000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.62000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.65000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.68000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.71000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.74000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 + 1.77000000000000e+02 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 + 1.80000000000000e+02 1.00000000000000e-04 3.50000000000000e-01 -1.00000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_01.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_01.dat index 2648f90a..955790ec 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_01.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_01.dat @@ -5,170 +5,216 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_01_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF01_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF01_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting -True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ - -28.000000 alpha0 ! 0-lift angle of attack, depends on airfoil. - 0.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -0.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - 0.000000 Cn2 ! As Cn1 for negative AOAs. -Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.350000 Cd0 ! 2D drag coefficient value at 0-lift. - -0.000100 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 9.99999999999994e-05 3.50000000000000e-01 -1.00000000000000e-04 --1.77714285740401e+02 1.00000000000003e-04 3.50000000000000e-01 -1.00000000000003e-04 --1.75428571400002e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.73142857116900e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.70857160423602e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.68571631778825e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.66285714267592e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.63999999984490e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.61714472886699e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.59428371284127e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.57142842639350e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.54857313994574e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.52571428568978e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.50285714285875e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.48000000002773e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.43857142836002e+02 1.00000000000044e-04 3.50000000000000e-01 -9.99999999999890e-05 --1.39714285726526e+02 1.00000000000044e-04 3.50000000000000e-01 -9.99999999999890e-05 --1.35571428559755e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.31428571450280e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.27285714283509e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.23142857116737e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.19000000007262e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.14857142840491e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.10714285731016e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.06571428564245e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --1.02428571454769e+02 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --9.82857142879980e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --9.41428571212269e+01 1.00000000000003e-04 3.50000000000000e-01 -9.99999999999890e-05 --9.00000000117516e+01 1.00000000000000e-04 3.50000000000000e-01 -9.99999999999890e-05 --8.58571428449804e+01 1.00000000000003e-04 3.50000000000000e-01 -9.99999999999890e-05 --8.17142857355051e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --7.75714285687340e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --7.34285714019628e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --6.92857142924875e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --6.51428571257163e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --6.10000000162410e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999890e-05 --5.68571428494699e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 --5.27142857399945e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 --4.85714285732234e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 --4.44285714064523e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 --4.02857142969769e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 --3.61428571302058e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 --3.20000000207304e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 --2.80000000253011e+01 9.99999999999890e-05 3.50000000000000e-01 -1.00000000000003e-04 --2.39999999725760e+01 9.99999999999890e-05 3.50000000000000e-01 -9.99999999999994e-05 --1.99999999771467e+01 9.99999999999890e-05 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b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_01_Coords.txt deleted file mode 100644 index 5d9f1607..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_01_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.490364 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -5.22832942930268e-16 - 9.99429683992583e-01 -2.22597407115582e-02 - 9.98063017832965e-01 -4.44580348954677e-02 - 9.95573914266674e-01 -6.65618134473914e-02 - 9.92086309749559e-01 -8.85198205325816e-02 - 9.87686148675057e-01 -1.10275272231260e-01 - 9.82330525170640e-01 -1.31784370919739e-01 - 9.76011908335692e-01 -1.53006617635088e-01 - 9.68787467298381e-01 -1.73886802805474e-01 - 9.60674860259240e-01 -1.94379348489358e-01 - 9.51675358763677e-01 -2.14449685889897e-01 - 9.41827652746244e-01 -2.34058378730561e-01 - 9.31175295355131e-01 -2.53152975865307e-01 - 9.19730397431178e-01 -2.71705871524177e-01 - 9.07524559194720e-01 -2.89691038427374e-01 - 8.94610408070308e-01 -3.07057540313714e-01 - 8.81009696499435e-01 -3.23779496057417e-01 - 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1.32872111539190e-01 -3.39428678290192e-01 - 1.23806439629760e-01 -3.29359452404754e-01 - 1.15147623386077e-01 -3.19202364510091e-01 - 1.06887208802748e-01 -3.08971834769008e-01 - 9.90071115215634e-02 -2.98675440643128e-01 - 9.15234043853439e-02 -2.88346537239591e-01 - 8.43970428172224e-02 -2.77979120522002e-01 - 7.76464790199521e-02 -2.67604205770439e-01 - 7.12479082120209e-02 -2.57229212452774e-01 - 6.51878662973747e-02 -2.46861090082763e-01 - 5.94874721274202e-02 -2.36524433012696e-01 - 5.41002464180900e-02 -2.26213901273871e-01 - 4.90378786701877e-02 -2.15949074862572e-01 - 4.43003497573338e-02 -2.05745246473815e-01 - 3.98423597346806e-02 -1.95597654428208e-01 - 3.56899752436130e-02 -1.85525503303304e-01 - 3.18292350050658e-02 -1.75535988753057e-01 - 2.82200072057899e-02 -1.65626936732462e-01 - 2.48925247792699e-02 -1.55815221490220e-01 - 2.18286683030034e-02 -1.46105621815703e-01 - 1.89846947131331e-02 -1.36495337998243e-01 - 1.63921917020335e-02 -1.26998300581103e-01 - 1.40446346341990e-02 -1.17620770590061e-01 - 1.18798249846349e-02 -1.08356847039079e-01 - 9.93094518736223e-03 -9.92166214620375e-02 - 8.21940795734749e-03 -9.02084101294225e-02 - 6.65838622137879e-03 -8.13254351098410e-02 - 5.26774192850643e-03 -7.25722234042700e-02 - 4.09515753852961e-03 -6.39564017315716e-02 - 3.09878859713640e-03 -5.54780130210999e-02 - 2.19660773551101e-03 -4.71320046999757e-02 - 1.46264176301869e-03 -3.89244052604170e-02 - 9.64484608297914e-04 -3.08606101713945e-02 - 5.99373867982851e-04 -2.29362359459691e-02 - 2.90086645599082e-04 -1.51487658773967e-02 - 7.80707788302466e-05 -7.50222207649338e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 7.50073622069008e-03 - 2.89878724192004e-04 1.51427584868874e-02 - 5.98775316682048e-04 2.29225845614194e-02 - 9.63326351634835e-04 3.08361193977748e-02 - 1.45966821282819e-03 3.88857489711792e-02 - 2.19097636449990e-03 4.70758159906831e-02 - 3.08997841959778e-03 5.54008881281673e-02 - 4.08271112470316e-03 6.38548864368973e-02 - 5.24853124383664e-03 7.24426344646886e-02 - 6.63128223001261e-03 8.11642365969105e-02 - 8.18368429859057e-03 9.00120990085718e-02 - 9.88361416849065e-03 9.89814202866229e-02 - 1.18176401547236e-02 1.08079023747493e-01 - 1.39661993216829e-02 1.17296891553284e-01 - 1.62951420791042e-02 1.26624818507885e-01 - 1.88631937781153e-02 1.36068234819796e-01 - 2.16807137532775e-02 1.45621741073938e-01 - 2.47159162958630e-02 1.55271505652796e-01 - 2.80064400105862e-02 1.65019126539152e-01 - 3.15762558914965e-02 1.74861450420233e-01 - 3.53948396168776e-02 1.84781748500356e-01 - 3.94949825480075e-02 1.94780451150684e-01 - 4.38979282781582e-02 2.04852826049369e-01 - 4.85758075737765e-02 2.14979335736815e-01 - 5.35679916138119e-02 2.25163248876704e-01 - 5.88818211488708e-02 2.35392575398327e-01 - 6.45001629027312e-02 2.45645861854957e-01 - 7.04692046391145e-02 2.55928809695428e-01 - 7.67740309924711e-02 2.66220088966340e-01 - 8.34162127168367e-02 2.76507393790272e-01 - 9.04290195190654e-02 2.86789711779561e-01 - 9.77906533229447e-02 2.97034361595414e-01 - 1.05536187198748e-01 3.07245770330167e-01 - 1.13658760041779e-01 3.17397798197942e-01 - 1.22161483318940e-01 3.27472514118938e-01 - 1.31067498602735e-01 3.37467155091885e-01 - 1.40354649921884e-01 3.47346400530541e-01 - 1.50055110786138e-01 3.57117293892256e-01 - 1.60148962661562e-01 3.66736829146265e-01 - 1.70658187899640e-01 3.76209016178366e-01 - 1.81574957422924e-01 3.85495420277773e-01 - 1.92907571409635e-01 3.94583247665971e-01 - 2.04657634577812e-01 4.03452252859203e-01 - 2.16817353069425e-01 4.12073654675103e-01 - 2.29396483963478e-01 4.20441260405522e-01 - 2.42377800694080e-01 4.28515729124923e-01 - 2.55773624268338e-01 4.36297014051329e-01 - 2.69566785632899e-01 4.43730784236712e-01 - 2.83765797226135e-01 4.50825718973627e-01 - 2.98347982887804e-01 4.57529313046837e-01 - 3.13318978785268e-01 4.63848274999177e-01 - 3.28658461892810e-01 4.69727033948470e-01 - 3.44364941645546e-01 4.75166089488011e-01 - 3.60419773725681e-01 4.80124895665173e-01 - 3.76811233766957e-01 4.84580156948735e-01 - 3.93525251020729e-01 4.88538023799543e-01 - 4.10538642553571e-01 4.91916286871980e-01 - 4.27843232490823e-01 4.94793689772683e-01 - 4.45406663468198e-01 4.97001865465950e-01 - 4.63222254103030e-01 4.98694527925836e-01 - 4.81251545655716e-01 4.99575957461702e-01 - 4.99481026671737e-01 4.99999595958852e-01 - 5.17879583085697e-01 4.99609899963933e-01 - 5.36417631367010e-01 4.98719254404591e-01 - 5.55075704909560e-01 4.96947095459801e-01 - 5.73808427242608e-01 4.94546807361687e-01 - 5.92596731105059e-01 4.91342495584800e-01 - 6.11401377553511e-01 4.87427713678203e-01 - 6.30186430605241e-01 4.82763790791591e-01 - 6.48926781663159e-01 4.77299436027394e-01 - 6.67570206424973e-01 4.71090906382616e-01 - 6.86088429590952e-01 4.64085564448580e-01 - 7.04445389043917e-01 4.56285153530383e-01 - 7.22592093722966e-01 4.47721154132331e-01 - 7.40501800453524e-01 4.38357128523673e-01 - 7.58125457122835e-01 4.28212344239085e-01 - 7.75421014376153e-01 4.17302884275069e-01 - 7.92362373587600e-01 4.05613976111210e-01 - 8.08894546151696e-01 3.93173546991026e-01 - 8.24974633014891e-01 3.79990391949436e-01 - 8.40576952273409e-01 3.66062639074102e-01 - 8.55652758808818e-01 3.51433146523418e-01 - 8.70162898882712e-01 3.36117863695803e-01 - 8.84085033071272e-01 3.20125614835584e-01 - 8.97361214262371e-01 3.03490505958309e-01 - 9.09954680076662e-01 2.86240968660934e-01 - 9.21851471402547e-01 2.68396507929684e-01 - 9.33012836658427e-01 2.50001405518451e-01 - 9.43389278969050e-01 2.31088842332577e-01 - 9.52973153850560e-01 2.11684808241657e-01 - 9.61743130827061e-01 1.91832340326070e-01 - 9.69640690675464e-01 1.71577158818629e-01 - 9.76664215898664e-01 1.50951670528481e-01 - 9.82815077112014e-01 1.29995621032034e-01 - 9.88028440045103e-01 1.08765299158177e-01 - 9.92304836603751e-01 8.72999337504368e-02 - 9.95693518775914e-01 6.56397719044068e-02 - 9.98120489340015e-01 4.38394581414280e-02 - 9.99443037908705e-01 2.19496513968833e-02 - 1.00000000000000e+00 -5.26302389882222e-16 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02.dat index 9cf5c6cd..56f85273 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02.dat @@ -5,170 +5,216 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_02_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF02_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF02_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting -True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ - -3.804232 alpha0 ! 0-lift angle of attack, depends on airfoil. - 16.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -16.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.269552 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.203403 Cn2 ! As Cn1 for negative AOAs. -Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.335257 Cd0 ! 2D drag coefficient value at 0-lift. - -0.007288 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -3.10733322339192e-03 3.32113218241621e-01 -9.47387824355836e-05 --1.77714285740401e+02 9.96530170512267e-03 3.32213857239068e-01 1.16453540112206e-02 --1.75428571400002e+02 2.10240501283441e-02 3.31904746906446e-01 2.08947973996588e-02 --1.73142857116900e+02 3.62556817542749e-02 3.31398407170147e-01 2.46213132836627e-02 --1.70857160423602e+02 5.38979144062238e-02 3.30941174009274e-01 2.04920501616480e-02 --1.68571631778825e+02 7.21874248847443e-02 3.30651012356958e-01 1.57391488884122e-02 --1.66285714267592e+02 8.93664584739361e-02 3.30123659514795e-01 1.36309952709129e-02 --1.63999999984490e+02 1.03668205115949e-01 3.29041082914396e-01 1.11338478505522e-02 --1.61714472886699e+02 1.13331572425408e-01 3.28014781379437e-01 8.35991240520516e-03 --1.59428371284127e+02 1.17045849990908e-01 3.28066724066147e-01 5.89542676323044e-03 --1.57142842639350e+02 1.15295045060673e-01 3.29524419057191e-01 2.48300175451564e-03 --1.54857313994574e+02 1.09016012377021e-01 3.32629395186724e-01 9.98653809981917e-04 --1.52571428568978e+02 9.91421399289329e-02 3.36671060375459e-01 9.32082745101953e-04 --1.50285714285875e+02 8.71951343725221e-02 3.40859774615473e-01 8.64567813082237e-04 --1.48000000002773e+02 7.62319845040279e-02 3.47092718827112e-01 8.08128219007914e-04 --1.43857142836002e+02 6.86877495348313e-02 3.52493312321350e-01 6.53796665304483e-04 --1.39714285726526e+02 6.44594616475228e-02 3.60164055807979e-01 5.63460185433198e-04 --1.35571428559755e+02 5.97890355335169e-02 3.67934143140940e-01 5.33773871696050e-04 --1.31428571450280e+02 5.47416405557487e-02 3.75699511590070e-01 5.26897242800743e-04 --1.27285714283509e+02 4.93831462096330e-02 3.83376108250419e-01 5.34015717079707e-04 --1.23142857116737e+02 4.37800042887829e-02 3.90884293082826e-01 5.52865014697507e-04 --1.19000000007262e+02 3.79991018963460e-02 3.98145913752279e-01 5.80013169191949e-04 --1.14857142840491e+02 3.21075973832993e-02 4.05083570699543e-01 6.11563683748720e-04 --1.10714285731016e+02 2.61727573392506e-02 4.11620478705874e-01 6.43361418563956e-04 --1.06571428564245e+02 2.02618224740247e-02 4.17633590106482e-01 6.71493535603265e-04 --1.02428571454769e+02 1.44419791670314e-02 4.22811728881639e-01 6.93927372767647e-04 --9.82857142879980e+01 8.78073421324833e-03 4.26794794654963e-01 7.09106689282708e-04 --9.41428571212269e+01 3.34891137554912e-03 4.29221055777272e-01 7.15471160696174e-04 --9.00000000117516e+01 -8.06411507948445e-04 4.29826181310013e-01 7.09977337363957e-04 --8.58571428449804e+01 -6.65148046261865e-03 4.28737633029783e-01 6.83620100725334e-04 --8.17142857355051e+01 -1.10405708931246e-02 4.26181237576670e-01 6.32371138369919e-04 --7.75714285687340e+01 -1.50256290401652e-02 4.22376295744486e-01 5.72158774515136e-04 --7.34285714019628e+01 -1.89603519208640e-02 4.17517263494615e-01 5.08758191994904e-04 --6.92857142924875e+01 -2.32630835730903e-02 4.11792294598547e-01 4.44026671246548e-04 --6.51428571257163e+01 -2.83554430471185e-02 4.05389316923582e-01 3.79797579786588e-04 --6.10000000162410e+01 -3.44965457300699e-02 3.98478059497202e-01 3.17986524005241e-04 --5.68571428494699e+01 -4.12659582062788e-02 3.91156441386406e-01 2.60812609036380e-04 --5.27142857399945e+01 -4.80601167219158e-02 3.83504862809438e-01 2.10112091317249e-04 --4.85714285732234e+01 -5.42636337224792e-02 3.75604548990577e-01 1.67245563989833e-04 --4.44285714064523e+01 -5.94701761508394e-02 3.67551519342678e-01 1.30613226332029e-04 --4.02857142969769e+01 -6.41046462042121e-02 3.59499602559543e-01 1.00683347708455e-04 --3.61428571302058e+01 -6.87888143933771e-02 3.51530574765216e-01 1.16259814740668e-04 --3.20000000207304e+01 -7.41390176941463e-02 3.47269071909602e-01 5.17447934267207e-03 --2.80000000253011e+01 -8.03158966384421e-02 3.48615565514332e-01 5.85799648421653e-03 --2.39999999725760e+01 -8.70208248165692e-02 3.43254331922963e-01 3.50277848891982e-03 --1.99999999771467e+01 -9.35204423742879e-02 3.37764879139166e-01 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9.00230260490811e-05 3.30798514504607e-01 -9.00230260490811e-05 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02_Coords.txt deleted file mode 100644 index d478731c..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.473446 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -1.45916500640515e-03 - 9.99429683992583e-01 -2.22105158334101e-02 - 9.98063017832965e-01 -4.25124962969033e-02 - 9.95573914266674e-01 -6.25952864646627e-02 - 9.92086309749559e-01 -8.25723443080139e-02 - 9.87686148675057e-01 -1.02404547939546e-01 - 9.82330525170640e-01 -1.22066455993314e-01 - 9.76011908335692e-01 -1.41534202688735e-01 - 9.68787467298381e-01 -1.60765906811600e-01 - 9.60674860259240e-01 -1.79726130161991e-01 - 9.51675358763677e-01 -1.98385258615741e-01 - 9.41827652746244e-01 -2.16700522943042e-01 - 9.31175295355131e-01 -2.34771866582841e-01 - 9.19730397431178e-01 -2.52385925665438e-01 - 9.07524559194720e-01 -2.69734380028305e-01 - 8.94610408070308e-01 -2.86604268454779e-01 - 8.81009696499435e-01 -3.02981722887499e-01 - 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1.32872111539190e-01 -3.33940106430249e-01 - 1.23806439629760e-01 -3.24157373537235e-01 - 1.15147623386077e-01 -3.14268638044843e-01 - 1.06887208802748e-01 -3.04325770640942e-01 - 9.90071115215634e-02 -2.94279872380243e-01 - 9.15234043853439e-02 -2.84212361778162e-01 - 8.43970428172224e-02 -2.74084654703535e-01 - 7.76464790199521e-02 -2.63937742227720e-01 - 7.12479082120209e-02 -2.53796781269782e-01 - 6.51878662973747e-02 -2.43629889379753e-01 - 5.94874721274202e-02 -2.33503795448512e-01 - 5.41002464180900e-02 -2.23408893913907e-01 - 4.90378786701877e-02 -2.13351268931510e-01 - 4.43003497573338e-02 -2.03372508377265e-01 - 3.98423597346806e-02 -1.93388807823141e-01 - 3.56899752436130e-02 -1.83483611054208e-01 - 3.18292350050658e-02 -1.73696360017908e-01 - 2.82200072057899e-02 -1.63914478774879e-01 - 2.48925247792699e-02 -1.54229402111553e-01 - 2.18286683030034e-02 -1.44642156541466e-01 - 1.89846947131331e-02 -1.35196689559653e-01 - 1.63921917020335e-02 -1.25831702110242e-01 - 1.40446346341990e-02 -1.16597162040537e-01 - 1.18798249846349e-02 -1.07494226852821e-01 - 9.93094518736223e-03 -9.84696569341336e-02 - 8.21940795734749e-03 -8.95729956289556e-02 - 6.65838622137879e-03 -8.07473218684967e-02 - 5.26774192850643e-03 -7.20041480258937e-02 - 4.09515753852961e-03 -6.33635198209369e-02 - 3.09878859713640e-03 -5.50059573640133e-02 - 2.19660773551101e-03 -4.65561514890715e-02 - 1.46264176301869e-03 -3.84168316276061e-02 - 9.64484608297914e-04 -3.04799416831861e-02 - 5.99373867982851e-04 -2.28525010193825e-02 - 2.90086645599082e-04 -1.51258353617900e-02 - 7.80707788302466e-05 -7.50080967033665e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 7.19913063899975e-03 - 2.89878724192004e-04 1.43377416108230e-02 - 5.98775316682048e-04 2.21507945193542e-02 - 9.63326351634835e-04 2.96818581994189e-02 - 1.45966821282819e-03 3.76375379123670e-02 - 2.19097636449990e-03 4.57323683546980e-02 - 3.08997841959778e-03 5.41895917224213e-02 - 4.08271112470316e-03 6.25011055747579e-02 - 5.24853124383664e-03 7.12164802717036e-02 - 6.63128223001261e-03 7.99503613640550e-02 - 8.18368429859057e-03 8.87833420327484e-02 - 9.88361416849065e-03 9.76586715091811e-02 - 1.18176401547236e-02 1.06624383950054e-01 - 1.39661993216829e-02 1.15687708134610e-01 - 1.62951420791042e-02 1.24880667023159e-01 - 1.88631937781153e-02 1.34175187980451e-01 - 2.16807137532775e-02 1.43571613563353e-01 - 2.47159162958630e-02 1.53118126718022e-01 - 2.80064400105862e-02 1.62736908838839e-01 - 3.15762558914965e-02 1.72423159549926e-01 - 3.53948396168776e-02 1.82180853855199e-01 - 3.94949825480075e-02 1.92013731428676e-01 - 4.38979282781582e-02 2.01937227944280e-01 - 4.85758075737765e-02 2.11887129629387e-01 - 5.35679916138119e-02 2.21879793644941e-01 - 5.88818211488708e-02 2.31933581261283e-01 - 6.45001629027312e-02 2.42006362065108e-01 - 7.04692046391145e-02 2.52107812705523e-01 - 7.67740309924711e-02 2.62203298801347e-01 - 8.34162127168367e-02 2.72283839014075e-01 - 9.04290195190654e-02 2.82341239167566e-01 - 9.77906533229447e-02 2.92347984588395e-01 - 1.05536187198748e-01 3.02347891472710e-01 - 1.13658760041779e-01 3.12238015847315e-01 - 1.22161483318940e-01 3.22083517939564e-01 - 1.31067498602735e-01 3.31825150916588e-01 - 1.40354649921884e-01 3.41454457558608e-01 - 1.50055110786138e-01 3.50962316384025e-01 - 1.60148962661562e-01 3.60324778042464e-01 - 1.70658187899640e-01 3.69541652384274e-01 - 1.81574957422924e-01 3.78566003536238e-01 - 1.92907571409635e-01 3.87384201312498e-01 - 2.04657634577812e-01 3.95960606094906e-01 - 2.16817353069425e-01 4.04288439628741e-01 - 2.29396483963478e-01 4.12357583519792e-01 - 2.42377800694080e-01 4.20132442091774e-01 - 2.55773624268338e-01 4.27600310487375e-01 - 2.69566785632899e-01 4.34728114391101e-01 - 2.83765797226135e-01 4.41482928461327e-01 - 2.98347982887804e-01 4.47870309328260e-01 - 3.13318978785268e-01 4.53848481608266e-01 - 3.28658461892810e-01 4.59374080097760e-01 - 3.44364941645546e-01 4.64438231236016e-01 - 3.60419773725681e-01 4.69071319079828e-01 - 3.76811233766957e-01 4.73125096584026e-01 - 3.93525251020729e-01 4.76718358963745e-01 - 4.10538642553571e-01 4.79724080778657e-01 - 4.27843232490823e-01 4.82222775017987e-01 - 4.45406663468198e-01 4.84034989034211e-01 - 4.63222254103030e-01 4.85330615845337e-01 - 4.81251545655716e-01 4.85831914823325e-01 - 4.99481026671737e-01 4.85839442995816e-01 - 5.17879583085697e-01 4.85053099930619e-01 - 5.36417631367010e-01 4.83729990429030e-01 - 5.55075704909560e-01 4.81543115516540e-01 - 5.73808427242608e-01 4.78764022569220e-01 - 5.92596731105059e-01 4.75151511195157e-01 - 6.11401377553511e-01 4.70875262723700e-01 - 6.30186430605241e-01 4.65865665355066e-01 - 6.48926781663159e-01 4.60045316076890e-01 - 6.67570206424973e-01 4.53530245432683e-01 - 6.86088429590952e-01 4.46232033475535e-01 - 7.04445389043917e-01 4.38140334553126e-01 - 7.22592093722966e-01 4.29345439955803e-01 - 7.40501800453524e-01 4.19796229537918e-01 - 7.58125457122835e-01 4.09489028749271e-01 - 7.75421014376153e-01 3.98478240948827e-01 - 7.92362373587600e-01 3.86709139026998e-01 - 8.08894546151696e-01 3.74267271616976e-01 - 8.24974633014891e-01 3.61140311970339e-01 - 8.40576952273409e-01 3.47343191596329e-01 - 8.55652758808818e-01 3.32873408109780e-01 - 8.70162898882712e-01 3.17805251242826e-01 - 8.84085033071272e-01 3.02140996501811e-01 - 8.97361214262371e-01 2.85960045800234e-01 - 9.09954680076662e-01 2.69208247239786e-01 - 9.21851471402547e-01 2.51965309785409e-01 - 9.33012836658427e-01 2.34267684983493e-01 - 9.43389278969050e-01 2.16173531053230e-01 - 9.52973153850560e-01 1.97647722032567e-01 - 9.61743130827061e-01 1.78771586722306e-01 - 9.69640690675464e-01 1.59595112003991e-01 - 9.76664215898664e-01 1.40152015143589e-01 - 9.82815077112014e-01 1.20483099288588e-01 - 9.88028440045103e-01 1.00651734089756e-01 - 9.92304836603751e-01 8.06989648707833e-02 - 9.95693518775914e-01 6.06756856705499e-02 - 9.98120489340015e-01 4.06301131152314e-02 - 9.99443037908705e-01 2.06073749443195e-02 - 1.00000000000000e+00 6.19012388006063e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03.dat index dd1f8a86..b05bd98b 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03.dat @@ -5,170 +5,216 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_03_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF03_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF03_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting -True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ - -3.725782 alpha0 ! 0-lift angle of attack, depends on airfoil. - 16.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -16.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.625801 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.405675 Cn2 ! As Cn1 for negative AOAs. -Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.297394 Cd0 ! 2D drag coefficient value at 0-lift. - -0.024589 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -9.90333760981913e-03 2.87810411243847e-01 -3.20276493265823e-05 --1.77714285740401e+02 3.23738901852211e-02 2.88141820672635e-01 3.85948669357438e-02 --1.75428571400002e+02 6.82580148798180e-02 2.87176347645336e-01 6.98870918217224e-02 --1.73142857116900e+02 1.16402361888554e-01 2.85584492941384e-01 8.45122869774501e-02 --1.70857160423602e+02 1.71624592451630e-01 2.84154358151603e-01 7.15764975036473e-02 --1.68571631778825e+02 2.28739113419834e-01 2.83280324731631e-01 5.72990432078830e-02 --1.66285714267592e+02 2.82577735505641e-01 2.81686389673487e-01 5.08812823139230e-02 --1.63999999984490e+02 3.27943969071893e-01 2.78247510337098e-01 4.33177066206485e-02 --1.61714472886699e+02 3.59659025771306e-01 2.74809869029704e-01 3.50348628747244e-02 --1.59428371284127e+02 3.73863203079530e-01 2.76409371747860e-01 2.77924897119230e-02 --1.57142842639350e+02 3.71946106025940e-01 2.82292426747956e-01 1.80284147064836e-02 --1.54857313994574e+02 3.56625090887651e-01 2.93163327226223e-01 1.34984901164223e-02 --1.52571428568978e+02 3.30606953029816e-01 3.06911068330416e-01 1.27408765367592e-02 --1.50285714285875e+02 2.98145654874029e-01 3.21190222244697e-01 1.19644151903208e-02 --1.48000000002773e+02 2.60781945541437e-01 3.40932493422584e-01 1.12866054689923e-02 --1.43857142836002e+02 2.35282578000830e-01 3.59641040741215e-01 9.42130221122981e-03 --1.39714285726526e+02 2.20661740751234e-01 3.85427466294420e-01 8.31944537887965e-03 --1.35571428559755e+02 2.04585101934709e-01 4.11848076142086e-01 7.94953607539458e-03 --1.31428571450280e+02 1.87258479606919e-01 4.38337855605438e-01 7.85814794220365e-03 --1.27285714283509e+02 1.68895443181922e-01 4.64553262626413e-01 7.93863122546099e-03 --1.23142857116737e+02 1.49716005572576e-01 4.90199600799897e-01 8.16284330798735e-03 --1.19000000007262e+02 1.29944997748733e-01 5.14998640090742e-01 8.48823383981202e-03 --1.14857142840491e+02 1.09810254795767e-01 5.38680480158509e-01 8.86674004430117e-03 --1.10714285731016e+02 8.95408073627084e-02 5.60982023398391e-01 9.24743639029276e-03 --1.06571428564245e+02 6.93654021454597e-02 5.81490302772046e-01 9.58264316924106e-03 --1.02428571454769e+02 4.95121819930665e-02 5.99158812752210e-01 9.84774688471677e-03 --9.82857142879980e+01 3.02128387033823e-02 6.12761715907514e-01 1.00239711814405e-02 --9.41428571212269e+01 1.17357756005592e-02 6.21055121023110e-01 1.00924945037584e-02 --9.00000000117516e+01 -2.72700290113436e-03 6.23125935822560e-01 1.00170512103631e-02 --8.58571428449804e+01 -2.28766815861732e-02 6.19408504512327e-01 9.69127647077032e-03 --8.17142857355051e+01 -3.80565401510533e-02 6.10678642383927e-01 9.06742777084244e-03 --7.75714285687340e+01 -5.19016958980298e-02 5.97687151521995e-01 8.33397254802832e-03 --7.34285714019628e+01 -6.56336456152370e-02 5.81098707577812e-01 7.55980713077804e-03 --6.92857142924875e+01 -8.05476529240540e-02 5.61555447316417e-01 6.76752358247389e-03 --6.51428571257163e+01 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6.66837016727444e-05 2.84801209438855e-01 -6.66837016727444e-05 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03_Coords.txt deleted file mode 100644 index f21bfd3d..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.455178 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -4.55098337804279e-03 - 9.99429683992583e-01 -2.16491268322406e-02 - 9.98063017832965e-01 -3.75283168095404e-02 - 9.95573914266674e-01 -5.28308613029241e-02 - 9.92086309749559e-01 -6.80672785436938e-02 - 9.87686148675057e-01 -8.32721857998092e-02 - 9.82330525170640e-01 -9.84763365213769e-02 - 9.76011908335692e-01 -1.13701392653913e-01 - 9.68787467298381e-01 -1.28940139636505e-01 - 9.60674860259240e-01 -1.44182329167992e-01 - 9.51675358763677e-01 -1.59410053139007e-01 - 9.41827652746244e-01 -1.74572106006873e-01 - 9.31175295355131e-01 -1.90122237677946e-01 - 9.19730397431178e-01 -2.05415006250103e-01 - 9.07524559194720e-01 -2.21133932450745e-01 - 8.94610408070308e-01 -2.36695951915595e-01 - 8.81009696499435e-01 -2.52114044552580e-01 - 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1.32872111539190e-01 -3.18587222016586e-01 - 1.23806439629760e-01 -3.09540828586481e-01 - 1.15147623386077e-01 -3.00349758438738e-01 - 1.06887208802748e-01 -2.91143104926355e-01 - 9.90071115215634e-02 -2.81755560166581e-01 - 9.15234043853439e-02 -2.72367077415241e-01 - 8.43970428172224e-02 -2.62872057901010e-01 - 7.76464790199521e-02 -2.53331775257841e-01 - 7.12479082120209e-02 -2.43807602254073e-01 - 6.51878662973747e-02 -2.34188094707390e-01 - 5.94874721274202e-02 -2.24626281262193e-01 - 5.41002464180900e-02 -2.15103617404787e-01 - 4.90378786701877e-02 -2.05598840844061e-01 - 4.43003497573338e-02 -1.96207122086654e-01 - 3.98423597346806e-02 -1.86683810020238e-01 - 3.56899752436130e-02 -1.77243373247734e-01 - 3.18292350050658e-02 -1.67990206880566e-01 - 2.82200072057899e-02 -1.58587152604212e-01 - 2.48925247792699e-02 -1.49277454827091e-01 - 2.18286683030034e-02 -1.40054291556556e-01 - 1.89846947131331e-02 -1.31054618540955e-01 - 1.63921917020335e-02 -1.22067183202847e-01 - 1.40446346341990e-02 -1.13231848934934e-01 - 1.18798249846349e-02 -1.04561160331953e-01 - 9.93094518736223e-03 -9.58770995396247e-02 - 8.21940795734749e-03 -8.73139641628116e-02 - 6.65838622137879e-03 -7.87057478593900e-02 - 5.26774192850643e-03 -7.00799308249116e-02 - 4.09515753852961e-03 -6.14807132298951e-02 - 3.09878859713640e-03 -5.34448859787075e-02 - 2.19660773551101e-03 -4.48455514539537e-02 - 1.46264176301869e-03 -3.69158490621138e-02 - 9.64484608297914e-04 -2.93257035366171e-02 - 5.99373867982851e-04 -2.23843380423809e-02 - 2.90086645599082e-04 -1.48640690521812e-02 - 7.80707788302466e-05 -7.48270698878658e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 6.43398031602526e-03 - 2.89878724192004e-04 1.23830171399774e-02 - 5.98775316682048e-04 2.02262530651556e-02 - 9.63326351634835e-04 2.68496245000696e-02 - 1.45966821282819e-03 3.45380248916239e-02 - 2.19097636449990e-03 4.23726572569808e-02 - 3.08997841959778e-03 5.10822821649726e-02 - 4.08271112470316e-03 5.90446621623546e-02 - 5.24853124383664e-03 6.79654386642701e-02 - 6.63128223001261e-03 7.66481482559574e-02 - 8.18368429859057e-03 8.53602990650568e-02 - 9.88361416849065e-03 9.39422089769670e-02 - 1.18176401547236e-02 1.02539501832957e-01 - 1.39661993216829e-02 1.11186613418542e-01 - 1.62951420791042e-02 1.20002027499339e-01 - 1.88631937781153e-02 1.28890127297219e-01 - 2.16807137532775e-02 1.37861485239225e-01 - 2.47159162958630e-02 1.47090822292441e-01 - 2.80064400105862e-02 1.56337807820684e-01 - 3.15762558914965e-02 1.65594519895369e-01 - 3.53948396168776e-02 1.74906605890625e-01 - 3.94949825480075e-02 1.84285177326308e-01 - 4.38979282781582e-02 1.93787713577473e-01 - 4.85758075737765e-02 2.03256846806270e-01 - 5.35679916138119e-02 2.12736224687758e-01 - 5.88818211488708e-02 2.22306995457223e-01 - 6.45001629027312e-02 2.31883961527972e-01 - 7.04692046391145e-02 2.41484981002873e-01 - 7.67740309924711e-02 2.51047983116958e-01 - 8.34162127168367e-02 2.60570939665969e-01 - 9.04290195190654e-02 2.70031087060954e-01 - 9.77906533229447e-02 2.79411005158860e-01 - 1.05536187198748e-01 2.88836157818249e-01 - 1.13658760041779e-01 2.98045010581918e-01 - 1.22161483318940e-01 3.07274936537887e-01 - 1.31067498602735e-01 3.16349524905059e-01 - 1.40354649921884e-01 3.25316229234619e-01 - 1.50055110786138e-01 3.34131874509231e-01 - 1.60148962661562e-01 3.42812475169202e-01 - 1.70658187899640e-01 3.51348890690362e-01 - 1.81574957422924e-01 3.59677125568486e-01 - 1.92907571409635e-01 3.67781723370086e-01 - 2.04657634577812e-01 3.75595180158118e-01 - 2.16817353069425e-01 3.83156839382868e-01 - 2.29396483963478e-01 3.90448708305975e-01 - 2.42377800694080e-01 3.97443532922570e-01 - 2.55773624268338e-01 4.04102296123050e-01 - 2.69566785632899e-01 4.10436952716289e-01 - 2.83765797226135e-01 4.16328081314042e-01 - 2.98347982887804e-01 4.21903051053307e-01 - 3.13318978785268e-01 4.27018844799682e-01 - 3.28658461892810e-01 4.31658488250379e-01 - 3.44364941645546e-01 4.35793376729409e-01 - 3.60419773725681e-01 4.39603542989314e-01 - 3.76811233766957e-01 4.42679542679953e-01 - 3.93525251020729e-01 4.45375975427744e-01 - 4.10538642553571e-01 4.47473561751343e-01 - 4.27843232490823e-01 4.49055399117351e-01 - 4.45406663468198e-01 4.49922104119272e-01 - 4.63222254103030e-01 4.50274759091021e-01 - 4.81251545655716e-01 4.49879586006387e-01 - 4.99481026671737e-01 4.48918750485981e-01 - 5.17879583085697e-01 4.47216610056487e-01 - 5.36417631367010e-01 4.44907166189848e-01 - 5.55075704909560e-01 4.41784695103341e-01 - 5.73808427242608e-01 4.38154579996933e-01 - 5.92596731105059e-01 4.33640279894313e-01 - 6.11401377553511e-01 4.28572253867854e-01 - 6.30186430605241e-01 4.22815661018464e-01 - 6.48926781663159e-01 4.16238205160875e-01 - 6.67570206424973e-01 4.09083551453397e-01 - 6.86088429590952e-01 4.01187135602747e-01 - 7.04445389043917e-01 3.92512181703335e-01 - 7.22592093722966e-01 3.83276031851220e-01 - 7.40501800453524e-01 3.73396336838822e-01 - 7.58125457122835e-01 3.62819547091621e-01 - 7.75421014376153e-01 3.51683323167064e-01 - 7.92362373587600e-01 3.39845440640900e-01 - 8.08894546151696e-01 3.27517971192967e-01 - 8.24974633014891e-01 3.14642149762072e-01 - 8.40576952273409e-01 3.01270398920976e-01 - 8.55652758808818e-01 2.87298347675474e-01 - 8.70162898882712e-01 2.72930440435441e-01 - 8.84085033071272e-01 2.58154383283995e-01 - 8.97361214262371e-01 2.43152627927478e-01 - 9.09954680076662e-01 2.27683655450130e-01 - 9.21851471402547e-01 2.11964213462919e-01 - 9.33012836658427e-01 1.96012989550098e-01 - 9.43389278969050e-01 1.79946355998745e-01 - 9.52973153850560e-01 1.63587310287742e-01 - 9.61743130827061e-01 1.47106218675068e-01 - 9.69640690675464e-01 1.30563507496297e-01 - 9.76664215898664e-01 1.13996487316667e-01 - 9.82815077112014e-01 9.74489251160531e-02 - 9.88028440045103e-01 8.10017558841005e-02 - 9.92304836603751e-01 6.47007862184292e-02 - 9.95693518775914e-01 4.87373227149277e-02 - 9.98120489340015e-01 3.30381632861306e-02 - 9.99443037908705e-01 1.76045331511850e-02 - 1.00000000000000e+00 2.18896417226120e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04.dat index 77e44e9e..2ff06c6d 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04.dat @@ -5,170 +5,216 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_04_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF04_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF04_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting -True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ - -3.628943 alpha0 ! 0-lift angle of attack, depends on airfoil. - 16.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -16.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.036544 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.417246 Cn2 ! As Cn1 for negative AOAs. -Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.245983 Cd0 ! 2D drag coefficient value at 0-lift. - -0.045012 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -1.61491850707893e-02 2.31507189672933e-01 1.70749474940932e-04 --1.77714285740401e+02 5.61977798168315e-02 2.32084096933403e-01 6.77878456776658e-02 --1.75428571400002e+02 1.17886616756733e-01 2.30568461514050e-01 1.24582845118510e-01 --1.73142857116900e+02 1.97649265230569e-01 2.28044565160140e-01 1.55834784816148e-01 --1.70857160423602e+02 2.87834013579020e-01 2.25814263204186e-01 1.36707149312797e-01 --1.68571631778825e+02 3.80783845369589e-01 2.24579651182320e-01 1.15671426785499e-01 --1.66285714267592e+02 4.68870103279947e-01 2.22352631501762e-01 1.05804068938745e-01 --1.63999999984490e+02 5.44418018802000e-01 2.17134161662739e-01 9.42227902375700e-02 --1.61714472886699e+02 5.99781255995411e-01 2.11706512212088e-01 8.18190087576165e-02 --1.59428371284127e+02 6.29247255773280e-01 2.17812709305043e-01 7.12610954459635e-02 --1.57142842639350e+02 6.34780507626056e-01 2.30630916396851e-01 5.77362735617769e-02 --1.54857313994574e+02 6.20295734920398e-01 2.51185568993266e-01 5.07680456962513e-02 --1.52571428568978e+02 5.89691119948731e-01 2.76304466490548e-01 4.83175981497401e-02 --1.50285714285875e+02 5.48675845997345e-01 3.02464192461508e-01 4.57552337619869e-02 --1.48000000002773e+02 4.83078165781565e-01 3.35270956729242e-01 4.33397667938328e-02 --1.43857142836002e+02 4.37423001046802e-01 3.70955377627664e-01 3.66218406533071e-02 --1.39714285726526e+02 4.09697598099380e-01 4.17761026853712e-01 3.25941759531835e-02 --1.35571428559755e+02 3.79507849912718e-01 4.66285975717049e-01 3.11961778736664e-02 --1.31428571450280e+02 3.47184990154514e-01 5.15101305053672e-01 3.08180631293230e-02 --1.27285714283509e+02 3.13083950578853e-01 5.63455166976137e-01 3.10750573008513e-02 --1.23142857116737e+02 2.77579360775772e-01 6.10745042989809e-01 3.18612124756887e-02 --1.19000000007262e+02 2.41060579754975e-01 6.56418754579186e-01 3.30169468246021e-02 --1.14857142840491e+02 2.03926151531373e-01 6.99949587034995e-01 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3.94881162172094e-05 2.27151529245548e-01 -3.94881162172094e-05 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04_Coords.txt deleted file mode 100644 index 67e7b407..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.436181 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -7.39250978506529e-03 - 9.99429683992583e-01 -1.99678802145499e-02 - 9.98063017832965e-01 -3.07910455521251e-02 - 9.95573914266674e-01 -4.05801258577343e-02 - 9.92086309749559e-01 -5.02620896271906e-02 - 9.87686148675057e-01 -6.00012144905994e-02 - 9.82330525170640e-01 -6.99089960583519e-02 - 9.76011908335692e-01 -8.00661030828948e-02 - 9.68787467298381e-01 -9.05082632075829e-02 - 9.60674860259240e-01 -1.01254854799715e-01 - 9.51675358763677e-01 -1.12301094789443e-01 - 9.41827652746244e-01 -1.23586656858467e-01 - 9.31175295355131e-01 -1.35933472722166e-01 - 9.19730397431178e-01 -1.48256197103020e-01 - 9.07524559194720e-01 -1.61707958055336e-01 - 8.94610408070308e-01 -1.75351595671947e-01 - 8.81009696499435e-01 -1.89227371679188e-01 - 8.66747905197194e-01 -2.03248118648129e-01 - 8.51890258171205e-01 -2.17236079260989e-01 - 8.36469462621421e-01 -2.31251524288479e-01 - 8.20513485943698e-01 -2.45094343430156e-01 - 8.04073832217581e-01 -2.58675541194942e-01 - 7.87191529885653e-01 -2.72259323944817e-01 - 7.69897919101553e-01 -2.85488775074598e-01 - 7.52252341235159e-01 -2.98152874214230e-01 - 7.34291349178558e-01 -3.10390675298846e-01 - 7.16044924955764e-01 -3.22040415810404e-01 - 6.97571640033109e-01 -3.32921556409764e-01 - 6.78906186433687e-01 -3.42959701032661e-01 - 6.60080312620540e-01 -3.52426619476410e-01 - 6.41147517137212e-01 -3.60938450254253e-01 - 6.22137650968852e-01 -3.68654029440781e-01 - 6.03087998194415e-01 -3.75573452566800e-01 - 5.84045042118975e-01 -3.81691721273444e-01 - 5.65030897687003e-01 -3.87102696403003e-01 - 5.46088602779599e-01 -3.91774841500673e-01 - 5.27248673916899e-01 -3.95521772448813e-01 - 5.08535950506088e-01 -3.98554876123792e-01 - 4.89992355470388e-01 -4.00974042818001e-01 - 4.71632114506831e-01 -4.02459163491619e-01 - 4.53492503744347e-01 -4.03515839568104e-01 - 4.35593302897673e-01 -4.03667156137102e-01 - 4.17956065616942e-01 -4.03210271727061e-01 - 4.00609748442576e-01 -4.02225602351876e-01 - 3.83560931606009e-01 -4.00725029475043e-01 - 3.66843215733716e-01 -3.98616889989439e-01 - 3.50457316320503e-01 -3.95891042970928e-01 - 3.34434484008630e-01 -3.92905041319025e-01 - 3.18774100329315e-01 -3.89194149713627e-01 - 3.03499623121295e-01 -3.85134309666510e-01 - 2.88611293565648e-01 -3.80654512046246e-01 - 2.74124386665666e-01 -3.75952810707021e-01 - 2.60041455523719e-01 -3.70601653896998e-01 - 2.46374872015917e-01 -3.65065758317139e-01 - 2.33123443938834e-01 -3.59077954358596e-01 - 2.20293777810423e-01 -3.52986100519001e-01 - 2.07883282965331e-01 -3.46513161449271e-01 - 1.95902956391646e-01 -3.39769062629550e-01 - 1.84341253066628e-01 -3.32858506696569e-01 - 1.73213930954160e-01 -3.25575569460296e-01 - 1.62499176129638e-01 -3.18265764689063e-01 - 1.52214602777260e-01 -3.10624404689251e-01 - 1.42331759398971e-01 -3.02893621760765e-01 - 1.32872111539190e-01 -2.95010862700140e-01 - 1.23806439629760e-01 -2.86967986006805e-01 - 1.15147623386077e-01 -2.78744783627330e-01 - 1.06887208802748e-01 -2.70535177100600e-01 - 9.90071115215634e-02 -2.62076163398663e-01 - 9.15234043853439e-02 -2.53629002905414e-01 - 8.43970428172224e-02 -2.45032114905338e-01 - 7.76464790199521e-02 -2.36363046647589e-01 - 7.12479082120209e-02 -2.27712786906889e-01 - 6.51878662973747e-02 -2.18904015128927e-01 - 5.94874721274202e-02 -2.10161131537852e-01 - 5.41002464180900e-02 -2.01457716943586e-01 - 4.90378786701877e-02 -1.92750641063822e-01 - 4.43003497573338e-02 -1.84178901984264e-01 - 3.98423597346806e-02 -1.75366796480766e-01 - 3.56899752436130e-02 -1.66636260209155e-01 - 3.18292350050658e-02 -1.58143060199878e-01 - 2.82200072057899e-02 -1.49366684884010e-01 - 2.48925247792699e-02 -1.40674615095215e-01 - 2.18286683030034e-02 -1.32053047235393e-01 - 1.89846947131331e-02 -1.23709596700394e-01 - 1.63921917020335e-02 -1.15318432006288e-01 - 1.40446346341990e-02 -1.07095666914975e-01 - 1.18798249846349e-02 -9.90555735859888e-02 - 9.93094518736223e-03 -9.09280099829789e-02 - 8.21940795734749e-03 -8.29192927862573e-02 - 6.65838622137879e-03 -7.47546770862440e-02 - 5.26774192850643e-03 -6.64795472529566e-02 - 4.09515753852961e-03 -5.81557664919994e-02 - 3.09878859713640e-03 -5.05837064337626e-02 - 2.19660773551101e-03 -4.20248004355329e-02 - 1.46264176301869e-03 -3.44531065595952e-02 - 9.64484608297914e-04 -2.73798120597959e-02 - 5.99373867982851e-04 -2.12198476862294e-02 - 2.90086645599082e-04 -1.40787314360443e-02 - 7.80707788302466e-05 -7.41747058669543e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 5.41688093698949e-03 - 2.89878724192004e-04 1.00136105195645e-02 - 5.98775316682048e-04 1.77475229842492e-02 - 9.63326351634835e-04 2.33217347768799e-02 - 1.45966821282819e-03 3.05786861241910e-02 - 2.19097636449990e-03 3.80215532667605e-02 - 3.08997841959778e-03 4.68726397124333e-02 - 4.08271112470316e-03 5.43991615476722e-02 - 5.24853124383664e-03 6.33267572268099e-02 - 6.63128223001261e-03 7.17606383410205e-02 - 8.18368429859057e-03 8.01313670934005e-02 - 9.88361416849065e-03 8.82030021610564e-02 - 1.18176401547236e-02 9.62355376306467e-02 - 1.39661993216829e-02 1.04274960153492e-01 - 1.62951420791042e-02 1.12510593212534e-01 - 1.88631937781153e-02 1.20794305474300e-01 - 2.16807137532775e-02 1.29140979271761e-01 - 2.47159162958630e-02 1.37827723077506e-01 - 2.80064400105862e-02 1.46481459608328e-01 - 3.15762558914965e-02 1.55092322200313e-01 - 3.53948396168776e-02 1.63738188317774e-01 - 3.94949825480075e-02 1.72437802844488e-01 - 4.38979282781582e-02 1.81285068442767e-01 - 4.85758075737765e-02 1.90041857387381e-01 - 5.35679916138119e-02 1.98775499285857e-01 - 5.88818211488708e-02 2.07620228367342e-01 - 6.45001629027312e-02 2.16453649327806e-01 - 7.04692046391145e-02 2.25300423247838e-01 - 7.67740309924711e-02 2.34075525584020e-01 - 8.34162127168367e-02 2.42783015382950e-01 - 9.04290195190654e-02 2.51388608403449e-01 - 9.77906533229447e-02 2.59881861724624e-01 - 1.05536187198748e-01 2.68457530696688e-01 - 1.13658760041779e-01 2.76721138029486e-01 - 1.22161483318940e-01 2.85056082709665e-01 - 1.31067498602735e-01 2.93186385093227e-01 - 1.40354649921884e-01 3.01207494544197e-01 - 1.50055110786138e-01 3.09045941978787e-01 - 1.60148962661562e-01 3.16752801803187e-01 - 1.70658187899640e-01 3.24310691929187e-01 - 1.81574957422924e-01 3.31642680715300e-01 - 1.92907571409635e-01 3.38731526965715e-01 - 2.04657634577812e-01 3.45482935872560e-01 - 2.16817353069425e-01 3.51976611897492e-01 - 2.29396483963478e-01 3.58188613842949e-01 - 2.42377800694080e-01 3.64100275501762e-01 - 2.55773624268338e-01 3.69650198663937e-01 - 2.69566785632899e-01 3.74890899517938e-01 - 2.83765797226135e-01 3.79629420427053e-01 - 2.98347982887804e-01 3.84099644273530e-01 - 3.13318978785268e-01 3.88071363163031e-01 - 3.28658461892810e-01 3.91552801712602e-01 - 3.44364941645546e-01 3.94498052164477e-01 - 3.60419773725681e-01 3.97219776927229e-01 - 3.76811233766957e-01 3.99083651805354e-01 - 3.93525251020729e-01 4.00648199092249e-01 - 4.10538642553571e-01 4.01618627899485e-01 - 4.27843232490823e-01 4.02077344876622e-01 - 4.45406663468198e-01 4.01816738332533e-01 - 4.63222254103030e-01 4.01057648276650e-01 - 4.81251545655716e-01 3.99621173666585e-01 - 4.99481026671737e-01 3.97567352696478e-01 - 5.17879583085697e-01 3.94850086889626e-01 - 5.36417631367010e-01 3.91478360244514e-01 - 5.55075704909560e-01 3.87375159716850e-01 - 5.73808427242608e-01 3.82863148884317e-01 - 5.92596731105059e-01 3.77454976240086e-01 - 6.11401377553511e-01 3.71621345607267e-01 - 6.30186430605241e-01 3.65171069940433e-01 - 6.48926781663159e-01 3.57925496057676e-01 - 6.67570206424973e-01 3.50242607318715e-01 - 6.86088429590952e-01 3.41890863127394e-01 - 7.04445389043917e-01 3.32808964224752e-01 - 7.22592093722966e-01 3.23331033205230e-01 - 7.40501800453524e-01 3.13347438304978e-01 - 7.58125457122835e-01 3.02758751935580e-01 - 7.75421014376153e-01 2.91779699378063e-01 - 7.92362373587600e-01 2.80186188421614e-01 - 8.08894546151696e-01 2.68309997572791e-01 - 8.24974633014891e-01 2.56048412714047e-01 - 8.40576952273409e-01 2.43490616798462e-01 - 8.55652758808818e-01 2.30431535318747e-01 - 8.70162898882712e-01 2.17202329325190e-01 - 8.84085033071272e-01 2.03776374746014e-01 - 8.97361214262371e-01 1.90439475783378e-01 - 9.09954680076662e-01 1.76762369142956e-01 - 9.21851471402547e-01 1.63099609076622e-01 - 9.33012836658427e-01 1.49451287783639e-01 - 9.43389278969050e-01 1.35993718555179e-01 - 9.52973153850560e-01 1.22401700542072e-01 - 9.61743130827061e-01 1.08938013636249e-01 - 9.69640690675464e-01 9.56742442623998e-02 - 9.76664215898664e-01 8.26517459551485e-02 - 9.82815077112014e-01 6.99174626116174e-02 - 9.88028440045103e-01 5.75717014417391e-02 - 9.92304836603751e-01 4.56653915554325e-02 - 9.95693518775914e-01 3.47185771485155e-02 - 9.98120489340015e-01 2.43621062076105e-02 - 9.99443037908705e-01 1.45042649831320e-02 - 1.00000000000000e+00 4.27485670561763e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_05.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_05.dat index a75655a7..0df6afe9 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_05.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_05.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_05_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF05_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF05_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.521914 alpha0 ! 0-lift angle of attack, depends on airfoil. - 16.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -16.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-17.222993 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.373416 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.560429 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.670092 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.101387 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.190095 Cd0 ! 2D drag coefficient value at 0-lift. - -0.062493 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.182988 Cd0 ! 2D drag coefficient value at 0-lift. +-0.065386 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -1.97648606466236e-02 1.75435865147145e-01 5.51947656052236e-04 --1.77714285740401e+02 7.38520956693145e-02 1.76183877798353e-01 8.99806261131119e-02 --1.75428571400002e+02 1.54054470210026e-01 1.74559747302041e-01 1.67812209817425e-01 --1.73142857116900e+02 2.53759437099059e-01 1.71817103389511e-01 2.17034887931701e-01 --1.70857160423602e+02 3.64691784936762e-01 1.69504498259746e-01 2.01888977924651e-01 --1.68571631778825e+02 4.78569791225215e-01 1.68558253358773e-01 1.81478839281180e-01 --1.66285714267592e+02 5.87146527767020e-01 1.67002417887806e-01 1.70679506783991e-01 --1.63999999984490e+02 6.82118496566564e-01 1.62574559242602e-01 1.57944853336123e-01 --1.61714472886699e+02 7.55216506860136e-01 1.58184214229937e-01 1.44676340049745e-01 --1.59428371284127e+02 8.00241262290836e-01 1.70588783380414e-01 1.33806293971199e-01 --1.57142842639350e+02 8.19182151994683e-01 1.90852357126183e-01 1.21087351018823e-01 --1.54857313994574e+02 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1.70145295538027e-05 1.70511408351162e-01 -1.70145295538027e-05 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_05_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_05_Coords.txt deleted file mode 100644 index b2ebc753..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_05_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.417397 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -9.03744871323492e-03 - 9.99429683992583e-01 -1.71183162800390e-02 - 9.98063017832965e-01 -2.35075471890739e-02 - 9.95573914266674e-01 -2.86298806555121e-02 - 9.92086309749559e-01 -3.35802153829736e-02 - 9.87686148675057e-01 -3.86300164066487e-02 - 9.82330525170640e-01 -4.39513510212433e-02 - 9.76011908335692e-01 -4.96667670687295e-02 - 9.68787467298381e-01 -5.58430369215416e-02 - 9.60674860259240e-01 -6.25205842850658e-02 - 9.51675358763677e-01 -6.97044683573522e-02 - 9.41827652746244e-01 -7.73315801563062e-02 - 9.31175295355131e-01 -8.64275875981200e-02 - 9.19730397431178e-01 -9.57052074325085e-02 - 9.07524559194720e-01 -1.06485103685012e-01 - 8.94610408070308e-01 -1.17722226389470e-01 - 8.81009696499435e-01 -1.29474748630974e-01 - 8.66747905197194e-01 -1.41647015324563e-01 - 8.51890258171205e-01 -1.54036875459343e-01 - 8.36469462621421e-01 -1.66727502765714e-01 - 8.20513485943698e-01 -1.79479382283088e-01 - 8.04073832217581e-01 -1.92197116242608e-01 - 7.87191529885653e-01 -2.05198806666282e-01 - 7.69897919101553e-01 -2.18055923295966e-01 - 7.52252341235159e-01 -2.30527849966298e-01 - 7.34291349178558e-01 -2.42782884340490e-01 - 7.16044924955764e-01 -2.54618728376433e-01 - 6.97571640033109e-01 -2.65823253821406e-01 - 6.78906186433687e-01 -2.76303697705641e-01 - 6.60080312620540e-01 -2.86355955820851e-01 - 6.41147517137212e-01 -2.95536374339607e-01 - 6.22137650968852e-01 -3.04009641541473e-01 - 6.03087998194415e-01 -3.11755987610886e-01 - 5.84045042118975e-01 -3.18776750398595e-01 - 5.65030897687003e-01 -3.25146769459740e-01 - 5.46088602779599e-01 -3.30834796092014e-01 - 5.27248673916899e-01 -3.35639635288157e-01 - 5.08535950506088e-01 -3.39739001132665e-01 - 4.89992355470388e-01 -3.43278951908397e-01 - 4.71632114506831e-01 -3.45872334281511e-01 - 4.53492503744347e-01 -3.48071757998070e-01 - 4.35593302897673e-01 -3.49365138849650e-01 - 4.17956065616942e-01 -3.50058453941472e-01 - 4.00609748442576e-01 -3.50229826132649e-01 - 3.83560931606009e-01 -3.49909530267297e-01 - 3.66843215733716e-01 -3.48962727294194e-01 - 3.50457316320503e-01 -3.47397827469833e-01 - 3.34434484008630e-01 -3.45601209032818e-01 - 3.18774100329315e-01 -3.43050569732267e-01 - 3.03499623121295e-01 -3.40160567345776e-01 - 2.88611293565648e-01 -3.36855750829559e-01 - 2.74124386665666e-01 -3.33347104037827e-01 - 2.60041455523719e-01 -3.29150332464233e-01 - 2.46374872015917e-01 -3.24787840185487e-01 - 2.33123443938834e-01 -3.19953299659813e-01 - 2.20293777810423e-01 -3.15037571162174e-01 - 2.07883282965331e-01 -3.09723491338568e-01 - 1.95902956391646e-01 -3.04130590676205e-01 - 1.84341253066628e-01 -2.98380065543532e-01 - 1.73213930954160e-01 -2.92226848287299e-01 - 1.62499176129638e-01 -2.86071524312738e-01 - 1.52214602777260e-01 -2.79550876969725e-01 - 1.42331759398971e-01 -2.72945878320387e-01 - 1.32872111539190e-01 -2.66176826136795e-01 - 1.23806439629760e-01 -2.59234824205363e-01 - 1.15147623386077e-01 -2.52092781436581e-01 - 1.06887208802748e-01 -2.44970694572502e-01 - 9.90071115215634e-02 -2.37566125422027e-01 - 9.15234043853439e-02 -2.30170700869196e-01 - 8.43970428172224e-02 -2.22600473662853e-01 - 7.76464790199521e-02 -2.14938189061722e-01 - 7.12479082120209e-02 -2.07285676976499e-01 - 6.51878662973747e-02 -1.99439833554642e-01 - 5.94874721274202e-02 -1.91652823537947e-01 - 5.41002464180900e-02 -1.83894409555376e-01 - 4.90378786701877e-02 -1.76114231047464e-01 - 4.43003497573338e-02 -1.68467986234262e-01 - 3.98423597346806e-02 -1.60530793270281e-01 - 3.56899752436130e-02 -1.52666010888346e-01 - 3.18292350050658e-02 -1.45046353075232e-01 - 2.82200072057899e-02 -1.37080555691005e-01 - 2.48925247792699e-02 -1.29184427457788e-01 - 2.18286683030034e-02 -1.21340432307845e-01 - 1.89846947131331e-02 -1.13774526570592e-01 - 1.63921917020335e-02 -1.06130076855324e-01 - 1.40446346341990e-02 -9.86583009916282e-02 - 1.18798249846349e-02 -9.13611974547854e-02 - 9.93094518736223e-03 -8.39484241363175e-02 - 8.21940795734749e-03 -7.66601997255550e-02 - 6.65838622137879e-03 -6.91424187619573e-02 - 5.26774192850643e-03 -6.14565903249468e-02 - 4.09515753852961e-03 -5.36696352298605e-02 - 3.09878859713640e-03 -4.66378574250911e-02 - 2.19660773551101e-03 -3.83851018624997e-02 - 1.46264176301869e-03 -3.12864712372292e-02 - 9.64484608297914e-04 -2.48308446169908e-02 - 5.99373867982851e-04 -1.93788900558350e-02 - 2.90086645599082e-04 -1.27441449163342e-02 - 7.80707788302466e-05 -7.27928245741744e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 4.33926848351473e-03 - 2.89878724192004e-04 7.85551165574490e-03 - 5.98775316682048e-04 1.52294941480008e-02 - 9.63326351634835e-04 1.99229686633255e-02 - 1.45966821282819e-03 2.66047732279115e-02 - 2.19097636449990e-03 3.35668631363089e-02 - 3.08997841959778e-03 4.23098673635364e-02 - 4.08271112470316e-03 4.94108219551294e-02 - 5.24853124383664e-03 5.80138018007133e-02 - 6.63128223001261e-03 6.59676861464639e-02 - 8.18368429859057e-03 7.37638530136619e-02 - 9.88361416849065e-03 8.11520232095434e-02 - 1.18176401547236e-02 8.84948443873072e-02 - 1.39661993216829e-02 9.58223283162200e-02 - 1.62951420791042e-02 1.03348873917140e-01 - 1.88631937781153e-02 1.10913059613264e-01 - 2.16807137532775e-02 1.18523724912165e-01 - 2.47159162958630e-02 1.26491545209070e-01 - 2.80064400105862e-02 1.34397556580526e-01 - 3.15762558914965e-02 1.42232221326523e-01 - 3.53948396168776e-02 1.50081273082795e-01 - 3.94949825480075e-02 1.57969127941874e-01 - 4.38979282781582e-02 1.66006198198400e-01 - 4.85758075737765e-02 1.73917624519575e-01 - 5.35679916138119e-02 1.81781596806773e-01 - 5.88818211488708e-02 1.89754034110419e-01 - 6.45001629027312e-02 1.97695907999662e-01 - 7.04692046391145e-02 2.05634444017349e-01 - 7.67740309924711e-02 2.13475715978082e-01 - 8.34162127168367e-02 2.21226663899695e-01 - 9.04290195190654e-02 2.28849822007676e-01 - 9.77906533229447e-02 2.36334807394053e-01 - 1.05536187198748e-01 2.43904765236584e-01 - 1.13658760041779e-01 2.51113790165816e-01 - 1.22161483318940e-01 2.58404743663472e-01 - 1.31067498602735e-01 2.65460777396448e-01 - 1.40354649921884e-01 2.72397877465190e-01 - 1.50055110786138e-01 2.79127746257371e-01 - 1.60148962661562e-01 2.85717725794222e-01 - 1.70658187899640e-01 2.92145888704554e-01 - 1.81574957422924e-01 2.98332916315834e-01 - 1.92907571409635e-01 3.04260431823823e-01 - 2.04657634577812e-01 3.09823903329053e-01 - 2.16817353069425e-01 3.15121482249306e-01 - 2.29396483963478e-01 3.20128203985311e-01 - 2.42377800694080e-01 3.24831607973540e-01 - 2.55773624268338e-01 3.29161348011340e-01 - 2.69566785632899e-01 3.33190351342357e-01 - 2.83765797226135e-01 3.36696480971823e-01 - 2.98347982887804e-01 3.39961373006520e-01 - 3.13318978785268e-01 3.42718294127892e-01 - 3.28658461892810e-01 3.44990691526994e-01 - 3.44364941645546e-01 3.46725079098120e-01 - 3.60419773725681e-01 3.48295825698358e-01 - 3.76811233766957e-01 3.48976258924282e-01 - 3.93525251020729e-01 3.49410350334756e-01 - 4.10538642553571e-01 3.49279752508864e-01 - 4.27843232490823e-01 3.48661322252976e-01 - 4.45406663468198e-01 3.47361166665188e-01 - 4.63222254103030e-01 3.45594971521664e-01 - 4.81251545655716e-01 3.43237843422371e-01 - 4.99481026671737e-01 3.40263895559983e-01 - 5.17879583085697e-01 3.36720639190598e-01 - 5.36417631367010e-01 3.32532910354611e-01 - 5.55075704909560e-01 3.27720324114763e-01 - 5.73808427242608e-01 3.22588985614079e-01 - 5.92596731105059e-01 3.16622088078526e-01 - 6.11401377553511e-01 3.10345845987816e-01 - 6.30186430605241e-01 3.03548320511874e-01 - 6.48926781663159e-01 2.96037172084798e-01 - 6.67570206424973e-01 2.88219691566919e-01 - 6.86088429590952e-01 2.79838834165453e-01 - 7.04445389043917e-01 2.70822788919541e-01 - 7.22592093722966e-01 2.61559669991881e-01 - 7.40501800453524e-01 2.51930121423408e-01 - 7.58125457122835e-01 2.41815087651037e-01 - 7.75421014376153e-01 2.31464435687833e-01 - 7.92362373587600e-01 2.20617058479895e-01 - 8.08894546151696e-01 2.09662242693245e-01 - 8.24974633014891e-01 1.98476435594736e-01 - 8.40576952273409e-01 1.87168299969463e-01 - 8.55652758808818e-01 1.75479758537078e-01 - 8.70162898882712e-01 1.63805705140497e-01 - 8.84085033071272e-01 1.52111526671448e-01 - 8.97361214262371e-01 1.40736127085253e-01 - 9.09954680076662e-01 1.29151773570059e-01 - 9.21851471402547e-01 1.17784859604979e-01 - 9.33012836658427e-01 1.06622642331442e-01 - 9.43389278969050e-01 9.58710007174688e-02 - 9.52973153850560e-01 8.51205240210637e-02 - 9.61743130827061e-01 7.46834993932264e-02 - 9.69640690675464e-01 6.46360934049478e-02 - 9.76664215898664e-01 5.50202415997049e-02 - 9.82815077112014e-01 4.58823980857935e-02 - 9.88028440045103e-01 3.73320180955541e-02 - 9.92304836603751e-01 2.94207238693901e-02 - 9.95693518775914e-01 2.29587060891190e-02 - 9.98120489340015e-01 1.73076701591211e-02 - 9.99443037908705e-01 1.23022284401015e-02 - 1.00000000000000e+00 6.48351522167481e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_06.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_06.dat index 39e183bb..290ca449 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_06.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_06.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_06_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF06_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF06_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.390975 alpha0 ! 0-lift angle of attack, depends on airfoil. - 14.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -14.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-15.195005 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.595797 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.671826 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.880382 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.203482 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.126617 Cd0 ! 2D drag coefficient value at 0-lift. - -0.075340 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.131200 Cd0 ! 2D drag coefficient value at 0-lift. +-0.075342 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -2.11261468349978e-02 1.18306188202563e-01 1.19678883492556e-03 --1.77714285740401e+02 8.42848264958898e-02 1.19117496130206e-01 1.03523939099369e-01 --1.75428571400002e+02 1.74961684478872e-01 1.18052664081305e-01 1.95424063350594e-01 --1.73142857116900e+02 2.83780946532269e-01 1.16194324763198e-01 2.60772509899272e-01 --1.70857160423602e+02 4.03022616621170e-01 1.14946707258396e-01 2.68782541655914e-01 --1.68571631778825e+02 5.24959714448935e-01 1.15367463620676e-01 2.58845486855361e-01 --1.66285714267592e+02 6.41902568261085e-01 1.16756549251010e-01 2.49959802610217e-01 --1.63999999984490e+02 7.46100853780073e-01 1.18068937884355e-01 2.39039721309594e-01 --1.61714472886699e+02 8.29840434870596e-01 1.21379273766440e-01 2.27996781718874e-01 --1.59428371284127e+02 8.87312968023319e-01 1.39771200265368e-01 2.19447465027284e-01 --1.57142842639350e+02 9.20215448294926e-01 1.66200299328029e-01 2.11298120319578e-01 --1.54857313994574e+02 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4.11424186832239e-06 1.23550153573951e-01 -4.11424186832239e-06 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_06_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_06_Coords.txt deleted file mode 100644 index d6478603..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_06_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.395727 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -9.65676109253199e-03 - 9.99429683992583e-01 -1.29081469766621e-02 - 9.98063017832965e-01 -1.52861879573635e-02 - 9.95573914266674e-01 -1.68422067556038e-02 - 9.92086309749559e-01 -1.82998465938938e-02 - 9.87686148675057e-01 -1.98896350530467e-02 - 9.82330525170640e-01 -2.17635501957756e-02 - 9.76011908335692e-01 -2.40329927841939e-02 - 9.68787467298381e-01 -2.67634574041222e-02 - 9.60674860259240e-01 -2.99967418112577e-02 - 9.51675358763677e-01 -3.37422314498872e-02 - 9.41827652746244e-01 -3.79493408525611e-02 - 9.31175295355131e-01 -4.35474351906958e-02 - 9.19730397431178e-01 -4.95045646211439e-02 - 9.07524559194720e-01 -5.67648622314190e-02 - 8.94610408070308e-01 -6.46440622214271e-02 - 8.81009696499435e-01 -7.32064640368920e-02 - 8.66747905197194e-01 -8.23849193501044e-02 - 8.51890258171205e-01 -9.20070565169486e-02 - 8.36469462621421e-01 -1.02161657115479e-01 - 8.20513485943698e-01 -1.12629153728257e-01 - 8.04073832217581e-01 -1.23322494365212e-01 - 7.87191529885653e-01 -1.34532309521309e-01 - 7.69897919101553e-01 -1.45863306422434e-01 - 7.52252341235159e-01 -1.57096948606635e-01 - 7.34291349178558e-01 -1.68383753256869e-01 - 7.16044924955764e-01 -1.79518930182681e-01 - 6.97571640033109e-01 -1.90288298966552e-01 - 6.78906186433687e-01 -2.00589406271790e-01 - 6.60080312620540e-01 -2.10661294065879e-01 - 6.41147517137212e-01 -2.20079349879013e-01 - 6.22137650968852e-01 -2.28966667371850e-01 - 6.03087998194415e-01 -2.37278597448181e-01 - 5.84045042118975e-01 -2.45003456271952e-01 - 5.65030897687003e-01 -2.52183090014745e-01 - 5.46088602779599e-01 -2.58781157955741e-01 - 5.27248673916899e-01 -2.64608742622371e-01 - 5.08535950506088e-01 -2.69788949912836e-01 - 4.89992355470388e-01 -2.74467562436677e-01 - 4.71632114506831e-01 -2.78272720722771e-01 - 4.53492503744347e-01 -2.81693260192149e-01 - 4.35593302897673e-01 -2.84271759967683e-01 - 4.17956065616942e-01 -2.86263607698390e-01 - 4.00609748442576e-01 -2.87733679298845e-01 - 3.83560931606009e-01 -2.88723278548804e-01 - 3.66843215733716e-01 -2.89093453261216e-01 - 3.50457316320503e-01 -2.88866392893547e-01 - 3.34434484008630e-01 -2.88387718643358e-01 - 3.18774100329315e-01 -2.87183805575820e-01 - 3.03499623121295e-01 -2.85632080258920e-01 - 2.88611293565648e-01 -2.83669690993933e-01 - 2.74124386665666e-01 -2.81480895741852e-01 - 2.60041455523719e-01 -2.78630743083486e-01 - 2.46374872015917e-01 -2.75595005987208e-01 - 2.33123443938834e-01 -2.72095001933339e-01 - 2.20293777810423e-01 -2.68491725473153e-01 - 2.07883282965331e-01 -2.64494741016215e-01 - 1.95902956391646e-01 -2.60215832024561e-01 - 1.84341253066628e-01 -2.55770407739142e-01 - 1.73213930954160e-01 -2.50929044503340e-01 - 1.62499176129638e-01 -2.46071370475522e-01 - 1.52214602777260e-01 -2.40850467199551e-01 - 1.42331759398971e-01 -2.35531959813724e-01 - 1.32872111539190e-01 -2.30041554472239e-01 - 1.23806439629760e-01 -2.24370969488596e-01 - 1.15147623386077e-01 -2.18496645433047e-01 - 1.06887208802748e-01 -2.12626121879498e-01 - 9.90071115215634e-02 -2.06475060840749e-01 - 9.15234043853439e-02 -2.00314984040753e-01 - 8.43970428172224e-02 -1.93972335881629e-01 - 7.76464790199521e-02 -1.87523935357076e-01 - 7.12479082120209e-02 -1.81064360018273e-01 - 6.51878662973747e-02 -1.74402826386607e-01 - 5.94874721274202e-02 -1.67777764271169e-01 - 5.41002464180900e-02 -1.61159120562166e-01 - 4.90378786701877e-02 -1.54503234754029e-01 - 4.43003497573338e-02 -1.47957696251029e-01 - 3.98423597346806e-02 -1.41123087127295e-01 - 3.56899752436130e-02 -1.34343729146006e-01 - 3.18292350050658e-02 -1.27778546384149e-01 - 2.82200072057899e-02 -1.20865367101957e-01 - 2.48925247792699e-02 -1.14000782276119e-01 - 2.18286683030034e-02 -1.07166240140345e-01 - 1.89846947131331e-02 -1.00559469348982e-01 - 1.63921917020335e-02 -9.38678739313066e-02 - 1.40446346341990e-02 -8.73432103984117e-02 - 1.18798249846349e-02 -8.09622514340960e-02 - 9.93094518736223e-03 -7.44760804371049e-02 - 8.21940795734749e-03 -6.81279924018791e-02 - 6.65838622137879e-03 -6.15010572507679e-02 - 5.26774192850643e-03 -5.46736079540193e-02 - 4.09515753852961e-03 -4.77101006279326e-02 - 3.09878859713640e-03 -4.13385896736058e-02 - 2.19660773551101e-03 -3.36666330293649e-02 - 1.46264176301869e-03 -2.71896945748771e-02 - 9.64484608297914e-04 -2.14978668645310e-02 - 5.99373867982851e-04 -1.67654498081870e-02 - 2.90086645599082e-04 -1.07646858285682e-02 - 7.80707788302466e-05 -7.01500814932453e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.14936992716049e-03 - 2.89878724192004e-04 5.99993200933650e-03 - 5.98775316682048e-04 1.25905269495867e-02 - 9.63326351634835e-04 1.66406657278569e-02 - 1.45966821282819e-03 2.25094587587553e-02 - 2.19097636449990e-03 2.88493966362323e-02 - 3.08997841959778e-03 3.71455945041225e-02 - 4.08271112470316e-03 4.38204163355225e-02 - 5.24853124383664e-03 5.16806340095531e-02 - 6.63128223001261e-03 5.88700178594897e-02 - 8.18368429859057e-03 6.58076747698291e-02 - 9.88361416849065e-03 7.22883261580368e-02 - 1.18176401547236e-02 7.87676216666191e-02 - 1.39661993216829e-02 8.52296685532063e-02 - 1.62951420791042e-02 9.18675645481044e-02 - 1.88631937781153e-02 9.85469215413348e-02 - 2.16807137532775e-02 1.05259349782793e-01 - 2.47159162958630e-02 1.12278559559801e-01 - 2.80064400105862e-02 1.19228506564741e-01 - 3.15762558914965e-02 1.26102143026935e-01 - 3.53948396168776e-02 1.32968039833682e-01 - 3.94949825480075e-02 1.39854582971291e-01 - 4.38979282781582e-02 1.46868738208547e-01 - 4.85758075737765e-02 1.53742980595814e-01 - 5.35679916138119e-02 1.60553633686758e-01 - 5.88818211488708e-02 1.67446434848495e-01 - 6.45001629027312e-02 1.74286413229669e-01 - 7.04692046391145e-02 1.81099021795666e-01 - 7.67740309924711e-02 1.87795805933505e-01 - 8.34162127168367e-02 1.94383405426206e-01 - 9.04290195190654e-02 2.00829943725539e-01 - 9.77906533229447e-02 2.07117856338881e-01 - 1.05536187198748e-01 2.13456437937483e-01 - 1.13658760041779e-01 2.19432922468120e-01 - 1.22161483318940e-01 2.25459934567297e-01 - 1.31067498602735e-01 2.31240703960086e-01 - 1.40354649921884e-01 2.36883248548869e-01 - 1.50055110786138e-01 2.42300403948284e-01 - 1.60148962661562e-01 2.47556218668006e-01 - 1.70658187899640e-01 2.52627933422976e-01 - 1.81574957422924e-01 2.57445232442984e-01 - 1.92907571409635e-01 2.61989277725017e-01 - 2.04657634577812e-01 2.66163010306180e-01 - 2.16817353069425e-01 2.70059996885415e-01 - 2.29396483963478e-01 2.73659625115426e-01 - 2.42377800694080e-01 2.76953335952365e-01 - 2.55773624268338e-01 2.79876332339319e-01 - 2.69566785632899e-01 2.82500603883500e-01 - 2.83765797226135e-01 2.84623010246538e-01 - 2.98347982887804e-01 2.86509613128005e-01 - 3.13318978785268e-01 2.87912290452998e-01 - 3.28658461892810e-01 2.88859511894231e-01 - 3.44364941645546e-01 2.89301215880378e-01 - 3.60419773725681e-01 2.89595456099091e-01 - 3.76811233766957e-01 2.89070849833410e-01 - 3.93525251020729e-01 2.88325032283705e-01 - 4.10538642553571e-01 2.87074934280835e-01 - 4.27843232490823e-01 2.85386285917212e-01 - 4.45406663468198e-01 2.83105736314987e-01 - 4.63222254103030e-01 2.80414787817664e-01 - 4.81251545655716e-01 2.77243939268909e-01 - 4.99481026671737e-01 2.73521932602366e-01 - 5.17879583085697e-01 2.69351067672779e-01 - 5.36417631367010e-01 2.64619508041508e-01 - 5.55075704909560e-01 2.59408912335490e-01 - 5.73808427242608e-01 2.53966108886345e-01 - 5.92596731105059e-01 2.47846874995901e-01 - 6.11401377553511e-01 2.41528256221525e-01 - 6.30186430605241e-01 2.34822471645022e-01 - 6.48926781663159e-01 2.27567132048163e-01 - 6.67570206424973e-01 2.20135758422315e-01 - 6.86088429590952e-01 2.12300746521561e-01 - 7.04445389043917e-01 2.04000605469263e-01 - 7.22592093722966e-01 1.95593752854008e-01 - 7.40501800453524e-01 1.86974889471329e-01 - 7.58125457122835e-01 1.78043145925974e-01 - 7.75421014376153e-01 1.69025086190160e-01 - 7.92362373587600e-01 1.59688449835853e-01 - 8.08894546151696e-01 1.50389859914096e-01 - 8.24974633014891e-01 1.41018907688053e-01 - 8.40576952273409e-01 1.31677560825713e-01 - 8.55652758808818e-01 1.22130021302292e-01 - 8.70162898882712e-01 1.12736995744562e-01 - 8.84085033071272e-01 1.03465015660722e-01 - 8.97361214262371e-01 9.46204347822092e-02 - 9.09954680076662e-01 8.57259962801082e-02 - 9.21851471402547e-01 7.71678154359447e-02 - 9.33012836658427e-01 6.89280221442882e-02 - 9.43389278969050e-01 6.11840463446998e-02 - 9.52973153850560e-01 5.35579061793152e-02 - 9.61743130827061e-01 4.63318029100362e-02 - 9.69640690675464e-01 3.95716829396008e-02 - 9.76664215898664e-01 3.33108605780830e-02 - 9.82815077112014e-01 2.75855964748786e-02 - 9.88028440045103e-01 2.24908080698501e-02 - 9.92304836603751e-01 1.80676319997101e-02 - 9.95693518775914e-01 1.49591813352759e-02 - 9.98120489340015e-01 1.26602173581683e-02 - 9.99443037908705e-01 1.10739641245597e-02 - 1.00000000000000e+00 8.92063788734677e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_07.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_07.dat index 64a5550e..9bd51a8a 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_07.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_07.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_07_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF07_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF07_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.293237 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-13.091020 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.637306 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.711302 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.951294 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.229081 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.084449 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079213 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.092737 Cd0 ! 2D drag coefficient value at 0-lift. +-0.078575 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -2.12211885772659e-02 8.41950990161022e-02 1.75327979613429e-03 --1.77714285740401e+02 8.61358778507013e-02 8.49663491590934e-02 1.06007865194836e-01 --1.75428571400002e+02 1.78583156724916e-01 8.47078735778045e-02 2.00713415083387e-01 --1.73142857116900e+02 2.88515019053329e-01 8.41727134923021e-02 2.71727267186176e-01 --1.70857160423602e+02 4.08484482278374e-01 8.44044579142382e-02 3.09059903980475e-01 --1.68571631778825e+02 5.31037540915245e-01 8.64464325062753e-02 3.11543085391330e-01 --1.66285714267592e+02 6.48757700668828e-01 9.13430904173475e-02 3.05286966733540e-01 --1.63999999984490e+02 7.54167486647088e-01 1.00137156510408e-01 2.96803955390831e-01 --1.61714472886699e+02 8.39825645305310e-01 1.13871164555097e-01 2.88257933292644e-01 --1.59428371284127e+02 9.00121400212648e-01 1.33753393122091e-01 2.81883476947179e-01 --1.57142842639350e+02 9.36641847656428e-01 1.61610011713182e-01 2.77324800283738e-01 --1.54857313994574e+02 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1.50621634755349e-07 9.14605754856553e-02 -1.50621634755349e-07 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_07_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_07_Coords.txt deleted file mode 100644 index 54aa8183..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_07_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.375529 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -9.70000000000000e-03 - 9.99429683992583e-01 -9.74344968733608e-03 - 9.98063017832965e-01 -9.85456018528176e-03 - 9.95573914266674e-01 -1.00816295833343e-02 - 9.92086309749559e-01 -1.04513500285802e-02 - 9.87686148675057e-01 -1.09987301771837e-02 - 9.82330525170640e-01 -1.17772607510065e-02 - 9.76011908335692e-01 -1.28380502966165e-02 - 9.68787467298381e-01 -1.42142205410083e-02 - 9.60674860259240e-01 -1.59302299429960e-02 - 9.51675358763677e-01 -1.79935902909063e-02 - 9.41827652746244e-01 -2.03752392526532e-02 - 9.31175295355131e-01 -2.37017214893818e-02 - 9.19730397431178e-01 -2.74751808940273e-02 - 9.07524559194720e-01 -3.19789003086019e-02 - 8.94610408070308e-01 -3.71305207991530e-02 - 8.81009696499435e-01 -4.29905615558843e-02 - 8.66747905197194e-01 -4.95395222529249e-02 - 8.51890258171205e-01 -5.66645708991310e-02 - 8.36469462621421e-01 -6.44449686595869e-02 - 8.20513485943698e-01 -7.27163621230752e-02 - 8.04073832217581e-01 -8.14057788021904e-02 - 7.87191529885653e-01 -9.07307000635042e-02 - 7.69897919101553e-01 -1.00388180500775e-01 - 7.52252341235159e-01 -1.10204619309800e-01 - 7.34291349178558e-01 -1.20286370459311e-01 - 7.16044924955764e-01 -1.30449547272861e-01 - 6.97571640033109e-01 -1.40494019982295e-01 - 6.78906186433687e-01 -1.50313191861276e-01 - 6.60080312620540e-01 -1.60061268678196e-01 - 6.41147517137212e-01 -1.69369641376018e-01 - 6.22137650968852e-01 -1.78306699556353e-01 - 6.03087998194415e-01 -1.86808620783241e-01 - 5.84045042118975e-01 -1.94843919131149e-01 - 5.65030897687003e-01 -2.02426220892904e-01 - 5.46088602779599e-01 -2.09512659008423e-01 - 5.27248673916899e-01 -2.15935758723872e-01 - 5.08535950506088e-01 -2.21773879847939e-01 - 4.89992355470388e-01 -2.27147671215725e-01 - 4.71632114506831e-01 -2.31737678916824e-01 - 4.53492503744347e-01 -2.35935869215281e-01 - 4.35593302897673e-01 -2.39364609491839e-01 - 4.17956065616942e-01 -2.42217680642936e-01 - 4.00609748442576e-01 -2.44546310186769e-01 - 3.83560931606009e-01 -2.46394769858158e-01 - 3.66843215733716e-01 -2.47641600225810e-01 - 3.50457316320503e-01 -2.48314760111503e-01 - 3.34434484008630e-01 -2.48700000000000e-01 - 3.18774100329315e-01 -2.48406800008598e-01 - 3.03499623121295e-01 -2.47751750167463e-01 - 2.88611293565648e-01 -2.46688240286034e-01 - 2.74124386665666e-01 -2.45364789633649e-01 - 2.60041455523719e-01 -2.43428709342608e-01 - 2.46374872015917e-01 -2.41276150352351e-01 - 2.33123443938834e-01 -2.38677870804955e-01 - 2.20293777810423e-01 -2.35941519494740e-01 - 2.07883282965331e-01 -2.32825210790137e-01 - 1.95902956391646e-01 -2.29427608931847e-01 - 1.84341253066628e-01 -2.25850221014578e-01 - 1.73213930954160e-01 -2.21898620347108e-01 - 1.62499176129638e-01 -2.17904608467404e-01 - 1.52214602777260e-01 -2.13565411210483e-01 - 1.42331759398971e-01 -2.09112729718007e-01 - 1.32872111539190e-01 -2.04485770783573e-01 - 1.23806439629760e-01 -1.99677179795072e-01 - 1.15147623386077e-01 -1.94669912007573e-01 - 1.06887208802748e-01 -1.89647519235976e-01 - 9.90071115215634e-02 -1.84360861049908e-01 - 9.15234043853439e-02 -1.79048033242285e-01 - 8.43970428172224e-02 -1.73555192252816e-01 - 7.76464790199521e-02 -1.67950809162290e-01 - 7.12479082120209e-02 -1.62317888355507e-01 - 6.51878662973747e-02 -1.56487866333058e-01 - 5.94874721274202e-02 -1.50674742233492e-01 - 5.41002464180900e-02 -1.44850295990460e-01 - 4.90378786701877e-02 -1.38980258418147e-01 - 4.43003497573338e-02 -1.33198569687942e-01 - 3.98423597346806e-02 -1.27147269628177e-01 - 3.56899752436130e-02 -1.21137772970021e-01 - 3.18292350050658e-02 -1.15310651994643e-01 - 2.82200072057899e-02 -1.09153745050063e-01 - 2.48925247792699e-02 -1.03029849153103e-01 - 2.18286683030034e-02 -9.69205865400306e-02 - 1.89846947131331e-02 -9.09918403551052e-02 - 1.63921917020335e-02 -8.49816940904262e-02 - 1.40446346341990e-02 -7.91324719011758e-02 - 1.18798249846349e-02 -7.34017240033564e-02 - 9.93094518736223e-03 -6.75827148677336e-02 - 8.21940795734749e-03 -6.19130127364097e-02 - 6.65838622137879e-03 -5.59363344186884e-02 - 5.26774192850643e-03 -4.97430094490934e-02 - 4.09515753852961e-03 -4.33970660566288e-02 - 3.09878859713640e-03 -3.74917604274478e-02 - 2.19660773551101e-03 -3.02799916443672e-02 - 1.46264176301869e-03 -2.42515862628895e-02 - 9.64484608297914e-04 -1.90981006077640e-02 - 5.99373867982851e-04 -1.48527350371945e-02 - 2.90086645599082e-04 -9.27005268921412e-03 - 7.80707788302466e-05 -6.76350835020684e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 2.37779354988049e-03 - 2.89878724192004e-04 5.15419050760589e-03 - 5.98775316682048e-04 1.09642261829148e-02 - 9.63326351634835e-04 1.48115515592183e-02 - 1.45966821282819e-03 2.00318835747579e-02 - 2.19097636449990e-03 2.59103096725312e-02 - 3.08997841959778e-03 3.37262082470834e-02 - 4.08271112470316e-03 4.01487971010596e-02 - 5.24853124383664e-03 4.73269967030886e-02 - 6.63128223001261e-03 5.39095097687308e-02 - 8.18368429859057e-03 6.01891259632789e-02 - 9.88361416849065e-03 6.60103134303056e-02 - 1.18176401547236e-02 7.18791804448717e-02 - 1.39661993216829e-02 7.77383782006727e-02 - 1.62951420791042e-02 8.37477951287289e-02 - 1.88631937781153e-02 8.98072485267033e-02 - 2.16807137532775e-02 9.58928679675489e-02 - 2.47159162958630e-02 1.02224592619658e-01 - 2.80064400105862e-02 1.08491840019242e-01 - 3.15762558914965e-02 1.14689843116871e-01 - 3.53948396168776e-02 1.20865759401746e-01 - 3.94949825480075e-02 1.27049703739391e-01 - 4.38979282781582e-02 1.33337797641980e-01 - 4.85758075737765e-02 1.39486256931644e-01 - 5.35679916138119e-02 1.45564781913115e-01 - 5.88818211488708e-02 1.51698791282280e-01 - 6.45001629027312e-02 1.57764903028482e-01 - 7.04692046391145e-02 1.63785554504065e-01 - 7.67740309924711e-02 1.69682050894831e-01 - 8.34162127168367e-02 1.75459472270113e-01 - 9.04290195190654e-02 1.81093379628753e-01 - 9.77906533229447e-02 1.86558632407653e-01 - 1.05536187198748e-01 1.92036778128565e-01 - 1.13658760041779e-01 1.97174000025855e-01 - 1.22161483318940e-01 2.02323281915305e-01 - 1.31067498602735e-01 2.07228209258692e-01 - 1.40354649921884e-01 2.11978739961904e-01 - 1.50055110786138e-01 2.16495850351431e-01 - 1.60148962661562e-01 2.20832391093474e-01 - 1.70658187899640e-01 2.24966789216130e-01 - 1.81574957422924e-01 2.28839619136839e-01 - 1.92907571409635e-01 2.32432100415119e-01 - 2.04657634577812e-01 2.35660261178648e-01 - 2.16817353069425e-01 2.38603900690895e-01 - 2.29396483963478e-01 2.41247650768891e-01 - 2.42377800694080e-01 2.43584220112568e-01 - 2.55773624268338e-01 2.45559300568650e-01 - 2.69566785632899e-01 2.47233869563075e-01 - 2.83765797226135e-01 2.48440199793708e-01 - 2.98347982887804e-01 2.49403540130172e-01 - 3.13318978785268e-01 2.49914599988337e-01 - 3.28658461892810e-01 2.50000000000000e-01 - 3.44364941645546e-01 2.49617589953471e-01 - 3.60419773725681e-01 2.49075529825292e-01 - 3.76811233766957e-01 2.47812179689320e-01 - 3.93525251020729e-01 2.46329079898305e-01 - 4.10538642553571e-01 2.44395169685389e-01 - 4.27843232490823e-01 2.42066759634389e-01 - 4.45406663468198e-01 2.39229619410123e-01 - 4.63222254103030e-01 2.36029419224241e-01 - 4.81251545655716e-01 2.32430740915831e-01 - 4.99481026671737e-01 2.28358140771565e-01 - 5.17879583085697e-01 2.23925479222289e-01 - 5.36417631367010e-01 2.19026669626907e-01 - 5.55075704909560e-01 2.13761268593993e-01 - 5.73808427242608e-01 2.08315870836875e-01 - 5.92596731105059e-01 2.02350369645377e-01 - 6.11401377553511e-01 1.96250490811855e-01 - 6.30186430605241e-01 1.89870019787972e-01 - 6.48926781663159e-01 1.83092269392735e-01 - 6.67570206424973e-01 1.76219381347811e-01 - 6.86088429590952e-01 1.69076300161838e-01 - 7.04445389043917e-01 1.61622430391087e-01 - 7.22592093722966e-01 1.54144458444941e-01 - 7.40501800453524e-01 1.46560909804285e-01 - 7.58125457122835e-01 1.38807841277349e-01 - 7.75421014376153e-01 1.31058627998205e-01 - 7.92362373587600e-01 1.23144448315184e-01 - 8.08894546151696e-01 1.15339631838483e-01 - 8.24974633014891e-01 1.07565538530738e-01 - 8.40576952273409e-01 9.99011788598178e-02 - 8.55652758808818e-01 9.21802006132661e-02 - 8.70162898882712e-01 8.46708105830004e-02 - 8.84085033071272e-01 7.73466083918915e-02 - 8.97361214262371e-01 7.04274277313195e-02 - 9.09954680076662e-01 6.35813799582239e-02 - 9.21851471402547e-01 5.70828092294470e-02 - 9.33012836658427e-01 5.09159918446133e-02 - 9.43389278969050e-01 4.51930005823538e-02 - 9.52973153850560e-01 3.96488077518718e-02 - 9.61743130827061e-01 3.44820895080033e-02 - 9.69640690675464e-01 2.97394395904186e-02 - 9.76664215898664e-01 2.54403125339494e-02 - 9.82815077112014e-01 2.16057418160031e-02 - 9.88028440045103e-01 1.83004499711868e-02 - 9.92304836603751e-01 1.55489221992466e-02 - 9.95693518775914e-01 1.33414608014433e-02 - 9.98120489340015e-01 1.17452004355877e-02 - 9.99443037908705e-01 1.08698313867193e-02 - 1.00000000000000e+00 1.05000000000000e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_08.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_08.dat index 9e9bc8a1..4e635a32 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_08.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_08.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_08_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF08_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF08_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.248635 alpha0 ! 0-lift angle of attack, depends on airfoil. - 12.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -12.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-11.833326 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.624254 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.717777 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.963699 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.243857 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.062280 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079780 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.068854 Cd0 ! 2D drag coefficient value at 0-lift. +-0.078768 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -1.67398533047094e-02 6.93841147514346e-02 2.47726881898942e-03 --1.77714285740401e+02 8.39758828377212e-02 6.92193384911768e-02 1.03391959145662e-01 --1.75428571400002e+02 1.73515840654821e-01 7.01386720863996e-02 1.97408197309845e-01 --1.73142857116900e+02 2.77370472023275e-01 7.13679306813170e-02 2.73006688083545e-01 --1.70857160423602e+02 3.89414243696378e-01 7.27822142552978e-02 3.28663314987939e-01 --1.68571631778825e+02 5.03529438147480e-01 7.51825556047519e-02 3.41267472689299e-01 --1.66285714267592e+02 6.13634665354171e-01 8.10313896581380e-02 3.37824028788822e-01 --1.63999999984490e+02 7.13591185837134e-01 9.42584836432143e-02 3.32311964534373e-01 --1.61714472886699e+02 7.97292140985912e-01 1.14033955159241e-01 3.27088545974825e-01 --1.59428371284127e+02 8.60158164770592e-01 1.36382254248430e-01 3.23777431849862e-01 --1.57142842639350e+02 9.03576180541895e-01 1.65785281504247e-01 3.24087238568257e-01 --1.54857313994574e+02 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0.00000000000000e+00 7.37956199987786e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_08_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_08_Coords.txt deleted file mode 100644 index 2537fbd6..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_08_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.361131 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -8.05795697370151e-03 - 9.99429683992583e-01 -7.29910462037433e-03 - 9.98063017832965e-01 -6.91557575315930e-03 - 9.95573914266674e-01 -6.93347821435899e-03 - 9.92086309749559e-01 -7.15267159661916e-03 - 9.87686148675057e-01 -7.53277402310766e-03 - 9.82330525170640e-01 -8.08297952904745e-03 - 9.76011908335692e-01 -8.82397530116188e-03 - 9.68787467298381e-01 -9.77119785400967e-03 - 9.60674860259240e-01 -1.09383005850174e-02 - 9.51675358763677e-01 -1.26809309010333e-02 - 9.41827652746244e-01 -1.45636325053422e-02 - 9.31175295355131e-01 -1.69972165245185e-02 - 9.19730397431178e-01 -1.99349956964491e-02 - 9.07524559194720e-01 -2.30389155664202e-02 - 8.94610408070308e-01 -2.67688462540916e-02 - 8.81009696499435e-01 -3.11756634069099e-02 - 8.66747905197194e-01 -3.62754155863396e-02 - 8.51890258171205e-01 -4.19960021821736e-02 - 8.36469462621421e-01 -4.84101006166521e-02 - 8.20513485943698e-01 -5.53993189072709e-02 - 8.04073832217581e-01 -6.28913763705476e-02 - 7.87191529885653e-01 -7.10433337127001e-02 - 7.69897919101553e-01 -7.96197453334471e-02 - 7.52252341235159e-01 -8.84958977548308e-02 - 7.34291349178558e-01 -9.77466466133717e-02 - 7.16044924955764e-01 -1.07213529869290e-01 - 6.97571640033109e-01 -1.16711213506436e-01 - 6.78906186433687e-01 -1.26134700105660e-01 - 6.60080312620540e-01 -1.35567568128049e-01 - 6.41147517137212e-01 -1.44701558011040e-01 - 6.22137650968852e-01 -1.53560937123849e-01 - 6.03087998194415e-01 -1.62072467101670e-01 - 5.84045042118975e-01 -1.70181302824929e-01 - 5.65030897687003e-01 -1.77896571800107e-01 - 5.46088602779599e-01 -1.85168867772548e-01 - 5.27248673916899e-01 -1.91856242310830e-01 - 5.08535950506088e-01 -1.98010171922887e-01 - 4.89992355470388e-01 -2.03716261997064e-01 - 4.71632114506831e-01 -2.08720872665178e-01 - 4.53492503744347e-01 -2.13317628501979e-01 - 4.35593302897673e-01 -2.17208264516542e-01 - 4.17956065616942e-01 -2.20523867416535e-01 - 4.00609748442576e-01 -2.23304955195919e-01 - 3.83560931606009e-01 -2.25594322719181e-01 - 3.66843215733716e-01 -2.27301374072467e-01 - 3.50457316320503e-01 -2.28453325477650e-01 - 3.34434484008630e-01 -2.29272645878498e-01 - 3.18774100329315e-01 -2.29461481096254e-01 - 3.03499623121295e-01 -2.29271924279608e-01 - 2.88611293565648e-01 -2.28671266746711e-01 - 2.74124386665666e-01 -2.27771349176189e-01 - 2.60041455523719e-01 -2.26314231315341e-01 - 2.46374872015917e-01 -2.24604414564064e-01 - 2.33123443938834e-01 -2.22468359379127e-01 - 2.20293777810423e-01 -2.20154171750093e-01 - 2.07883282965331e-01 -2.17476671989832e-01 - 1.95902956391646e-01 -2.14518997398475e-01 - 1.84341253066628e-01 -2.11366026535465e-01 - 1.73213930954160e-01 -2.07865873864485e-01 - 1.62499176129638e-01 -2.04292156193720e-01 - 1.52214602777260e-01 -2.00399334738711e-01 - 1.42331759398971e-01 -1.96373951228210e-01 - 1.32872111539190e-01 -1.92175125421068e-01 - 1.23806439629760e-01 -1.87794629353560e-01 - 1.15147623386077e-01 -1.83223541411133e-01 - 1.06887208802748e-01 -1.78617018837112e-01 - 9.90071115215634e-02 -1.73769527117248e-01 - 9.15234043853439e-02 -1.68878427053402e-01 - 8.43970428172224e-02 -1.63815230375681e-01 - 7.76464790199521e-02 -1.58638552023632e-01 - 7.12479082120209e-02 -1.53416333518084e-01 - 6.51878662973747e-02 -1.48010127197515e-01 - 5.94874721274202e-02 -1.42600739499363e-01 - 5.41002464180900e-02 -1.37162081975146e-01 - 4.90378786701877e-02 -1.31672165007772e-01 - 4.43003497573338e-02 -1.26246470026537e-01 - 3.98423597346806e-02 -1.20587158814771e-01 - 3.56899752436130e-02 -1.14957411868270e-01 - 3.18292350050658e-02 -1.09472713979138e-01 - 2.82200072057899e-02 -1.03697598999174e-01 - 2.48925247792699e-02 -9.79426278372568e-02 - 2.18286683030034e-02 -9.21904950104262e-02 - 1.89846947131331e-02 -8.65665949138775e-02 - 1.63921917020335e-02 -8.08732293154285e-02 - 1.40446346341990e-02 -7.53318659842251e-02 - 1.18798249846349e-02 -6.98859434447039e-02 - 9.93094518736223e-03 -6.43812564762668e-02 - 8.21940795734749e-03 -5.90391874038575e-02 - 6.65838622137879e-03 -5.33894769357009e-02 - 5.26774192850643e-03 -4.75290423483065e-02 - 4.09515753852961e-03 -4.15077297868053e-02 - 3.09878859713640e-03 -3.57709813285351e-02 - 2.19660773551101e-03 -2.87973912829915e-02 - 1.46264176301869e-03 -2.29464203278289e-02 - 9.64484608297914e-04 -1.79827519544071e-02 - 5.99373867982851e-04 -1.37971831337808e-02 - 2.90086645599082e-04 -8.18784029912156e-03 - 7.80707788302466e-05 -5.90717037484557e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.96982984950151e-03 - 2.89878724192004e-04 4.83730347638251e-03 - 5.98775316682048e-04 1.01513819113681e-02 - 9.63326351634835e-04 1.39824836573200e-02 - 1.45966821282819e-03 1.89040908265623e-02 - 2.19097636449990e-03 2.46873689497229e-02 - 3.08997841959778e-03 3.23516559490662e-02 - 4.08271112470316e-03 3.87563642512302e-02 - 5.24853124383664e-03 4.55714558762030e-02 - 6.63128223001261e-03 5.18473046215370e-02 - 8.18368429859057e-03 5.77859177822153e-02 - 9.88361416849065e-03 6.32844448978734e-02 - 1.18176401547236e-02 6.88823438892196e-02 - 1.39661993216829e-02 7.44821615138365e-02 - 1.62951420791042e-02 8.02127147654710e-02 - 1.88631937781153e-02 8.60035644117063e-02 - 2.16807137532775e-02 9.18165478989828e-02 - 2.47159162958630e-02 9.78179191655228e-02 - 2.80064400105862e-02 1.03764488988914e-01 - 3.15762558914965e-02 1.09654232184920e-01 - 3.53948396168776e-02 1.15514304227109e-01 - 3.94949825480075e-02 1.21374610931861e-01 - 4.38979282781582e-02 1.27317331841658e-01 - 4.85758075737765e-02 1.33128092660676e-01 - 5.35679916138119e-02 1.38868816260818e-01 - 5.88818211488708e-02 1.44639978054529e-01 - 6.45001629027312e-02 1.50333679834233e-01 - 7.04692046391145e-02 1.55967771695752e-01 - 7.67740309924711e-02 1.61474933830469e-01 - 8.34162127168367e-02 1.66859038089047e-01 - 9.04290195190654e-02 1.72103887205579e-01 - 9.77906533229447e-02 1.77174571932464e-01 - 1.05536187198748e-01 1.82221341728853e-01 - 1.13658760041779e-01 1.86957250473523e-01 - 1.22161483318940e-01 1.91668246837529e-01 - 1.31067498602735e-01 1.96142975405356e-01 - 1.40354649921884e-01 2.00448980102233e-01 - 1.50055110786138e-01 2.04518018870449e-01 - 1.60148962661562e-01 2.08387955189305e-01 - 1.70658187899640e-01 2.12042476431479e-01 - 1.81574957422924e-01 2.15429855865062e-01 - 1.92907571409635e-01 2.18531338459934e-01 - 2.04657634577812e-01 2.21279945324466e-01 - 2.16817353069425e-01 2.23733970768941e-01 - 2.29396483963478e-01 2.25887463213039e-01 - 2.42377800694080e-01 2.27727709007643e-01 - 2.55773624268338e-01 2.29215852783615e-01 - 2.69566785632899e-01 2.30394135719356e-01 - 2.83765797226135e-01 2.31136526735566e-01 - 2.98347982887804e-01 2.31618957788020e-01 - 3.13318978785268e-01 2.31674959147667e-01 - 3.28658461892810e-01 2.31322210040798e-01 - 3.44364941645546e-01 2.30529436849741e-01 - 3.60419773725681e-01 2.29544260633189e-01 - 3.76811233766957e-01 2.27927135609575e-01 - 3.93525251020729e-01 2.26070890014868e-01 - 4.10538642553571e-01 2.23793180614115e-01 - 4.27843232490823e-01 2.21149128249817e-01 - 4.45406663468198e-01 2.18050143624270e-01 - 4.63222254103030e-01 2.14614389414842e-01 - 4.81251545655716e-01 2.10821719950327e-01 - 4.99481026671737e-01 2.06613926638319e-01 - 5.17879583085697e-01 2.02088738620152e-01 - 5.36417631367010e-01 1.97166433713562e-01 - 5.55075704909560e-01 1.91939862133871e-01 - 5.73808427242608e-01 1.86546834712419e-01 - 5.92596731105059e-01 1.80743474129666e-01 - 6.11401377553511e-01 1.74827722161012e-01 - 6.30186430605241e-01 1.68691251527291e-01 - 6.48926781663159e-01 1.62256651616643e-01 - 6.67570206424973e-01 1.55762911803922e-01 - 6.86088429590952e-01 1.49076962247911e-01 - 7.04445389043917e-01 1.42176016160581e-01 - 7.22592093722966e-01 1.35283735141332e-01 - 7.40501800453524e-01 1.28335125701865e-01 - 7.58125457122835e-01 1.21299501770014e-01 - 7.75421014376153e-01 1.14301509190897e-01 - 7.92362373587600e-01 1.07223117687386e-01 - 8.08894546151696e-01 1.00269491848142e-01 - 8.24974633014891e-01 9.33931696724048e-02 - 8.40576952273409e-01 8.66500869240179e-02 - 8.55652758808818e-01 7.99259218514095e-02 - 8.70162898882712e-01 7.34206541524526e-02 - 8.84085033071272e-01 6.71094492709432e-02 - 8.97361214262371e-01 6.11546732920916e-02 - 9.09954680076662e-01 5.53296445696055e-02 - 9.21851471402547e-01 4.98303470582870e-02 - 9.33012836658427e-01 4.46414015366825e-02 - 9.43389278969050e-01 3.98318109101110e-02 - 9.52973153850560e-01 3.52131135553144e-02 - 9.61743130827061e-01 3.09329123469280e-02 - 9.69640690675464e-01 2.70286371015725e-02 - 9.76664215898664e-01 2.35125240820712e-02 - 9.82815077112014e-01 2.03931816839794e-02 - 9.88028440045103e-01 1.77116704905311e-02 - 9.92304836603751e-01 1.54605438025476e-02 - 9.95693518775914e-01 1.35081098434327e-02 - 9.98120489340015e-01 1.20721238538249e-02 - 9.99443037908705e-01 1.13056477175237e-02 - 1.00000000000000e+00 1.13344675832667e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_09.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_09.dat index fb317502..5fee76ce 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_09.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_09.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_09_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF09_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF09_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.205249 alpha0 ! 0-lift angle of attack, depends on airfoil. - 11.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -11.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-11.008829 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.601270 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.719713 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.959434 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.237959 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.041118 Cd0 ! 2D drag coefficient value at 0-lift. - -0.080046 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.045594 Cd0 ! 2D drag coefficient value at 0-lift. +-0.078754 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.25918400516756e-03 5.68952227603989e-02 3.54155557160406e-03 --1.77714285740401e+02 7.96612792570610e-02 5.54342323004533e-02 9.84270512646245e-02 --1.75428571400002e+02 1.63432906663201e-01 5.78041706375701e-02 1.91153262743349e-01 --1.73142857116900e+02 2.55346162695095e-01 6.11663752047571e-02 2.73940981309593e-01 --1.70857160423602e+02 3.51854432683337e-01 6.38481034788960e-02 3.46362664912529e-01 --1.68571631778825e+02 4.49439876631883e-01 6.63193362357069e-02 3.70810639848057e-01 --1.66285714267592e+02 5.44617893642041e-01 7.25231057927432e-02 3.71139076137085e-01 --1.63999999984490e+02 6.33853936059803e-01 8.96393697570427e-02 3.69863991109482e-01 --1.61714472886699e+02 7.13637662503012e-01 1.14342027016144e-01 3.69592350713131e-01 --1.59428371284127e+02 7.81370946999808e-01 1.41357222754677e-01 3.70991227467965e-01 --1.57142842639350e+02 8.37930241273888e-01 1.73686739480675e-01 3.78822986828390e-01 --1.54857313994574e+02 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0.00000000000000e+00 5.94864829366104e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_09_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_09_Coords.txt deleted file mode 100644 index ceea75ab..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_09_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.348751 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -4.95048497379648e-03 - 9.99429683992583e-01 -4.30895259836048e-03 - 9.98063017832965e-01 -4.07877720034152e-03 - 9.95573914266674e-01 -4.15891865517266e-03 - 9.92086309749559e-01 -4.37699448406590e-03 - 9.87686148675057e-01 -4.69202873392753e-03 - 9.82330525170640e-01 -5.10049965304712e-03 - 9.76011908335692e-01 -5.60896192363615e-03 - 9.68787467298381e-01 -6.22335545584829e-03 - 9.60674860259240e-01 -6.94994514509781e-03 - 9.51675358763677e-01 -8.63063896586801e-03 - 9.41827652746244e-01 -1.02553282537003e-02 - 9.31175295355131e-01 -1.20335040110229e-02 - 9.19730397431178e-01 -1.43703778246174e-02 - 9.07524559194720e-01 -1.62632247405561e-02 - 8.94610408070308e-01 -1.87363025293936e-02 - 8.81009696499435e-01 -2.18269323906868e-02 - 8.66747905197194e-01 -2.55854610803887e-02 - 8.51890258171205e-01 -2.99795635046985e-02 - 8.36469462621421e-01 -3.50753080201158e-02 - 8.20513485943698e-01 -4.08044704418940e-02 - 8.04073832217581e-01 -4.70936304782917e-02 - 7.87191529885653e-01 -5.40317432946095e-02 - 7.69897919101553e-01 -6.14577182093182e-02 - 7.52252341235159e-01 -6.93088811436222e-02 - 7.34291349178558e-01 -7.76266406211985e-02 - 7.16044924955764e-01 -8.62874880880659e-02 - 6.97571640033109e-01 -9.51287335104948e-02 - 6.78906186433687e-01 -1.04052820420110e-01 - 6.60080312620540e-01 -1.13059171302737e-01 - 6.41147517137212e-01 -1.21920892353227e-01 - 6.22137650968852e-01 -1.30610461754196e-01 - 6.03087998194415e-01 -1.39047023173058e-01 - 5.84045042118975e-01 -1.47146340430285e-01 - 5.65030897687003e-01 -1.54917034041653e-01 - 5.46088602779599e-01 -1.62301853652288e-01 - 5.27248673916899e-01 -1.69193983397169e-01 - 5.08535950506088e-01 -1.75616147481210e-01 - 4.89992355470388e-01 -1.81603536152660e-01 - 4.71632114506831e-01 -1.86995859567974e-01 - 4.53492503744347e-01 -1.91954817145008e-01 - 4.35593302897673e-01 -1.96288729714510e-01 - 4.17956065616942e-01 -2.00046447433552e-01 - 4.00609748442576e-01 -2.03255059961457e-01 - 3.83560931606009e-01 -2.05952956761210e-01 - 3.66843215733716e-01 -2.08095743274779e-01 - 3.50457316320503e-01 -2.09707182310284e-01 - 3.34434484008630e-01 -2.10923308234904e-01 - 3.18774100329315e-01 -2.11575067433108e-01 - 3.03499623121295e-01 -2.11825263273296e-01 - 2.88611293565648e-01 -2.11659706294056e-01 - 2.74124386665666e-01 -2.11140130854174e-01 - 2.60041455523719e-01 -2.10141497501254e-01 - 2.46374872015917e-01 -2.08839288762018e-01 - 2.33123443938834e-01 -2.07139015435273e-01 - 2.20293777810423e-01 -2.05203744182177e-01 - 2.07883282965331e-01 -2.02929308378739e-01 - 1.95902956391646e-01 -2.00376855049898e-01 - 1.84341253066628e-01 -1.97606477068258e-01 - 1.73213930954160e-01 -1.94529356875149e-01 - 1.62499176129638e-01 -1.91332332765327e-01 - 1.52214602777260e-01 -1.87856287923809e-01 - 1.42331759398971e-01 -1.84220373160268e-01 - 1.32872111539190e-01 -1.80413507777438e-01 - 1.23806439629760e-01 -1.76426396657033e-01 - 1.15147623386077e-01 -1.72262603352316e-01 - 1.06887208802748e-01 -1.68033592631753e-01 - 9.90071115215634e-02 -1.63601195163628e-01 - 9.15234043853439e-02 -1.59100898602050e-01 - 8.43970428172224e-02 -1.54443720866901e-01 - 7.76464790199521e-02 -1.49673746332692e-01 - 7.12479082120209e-02 -1.44835608533103e-01 - 6.51878662973747e-02 -1.39838602884260e-01 - 5.94874721274202e-02 -1.34811085776796e-01 - 5.41002464180900e-02 -1.29730534164918e-01 - 4.90378786701877e-02 -1.24593891937783e-01 - 4.43003497573338e-02 -1.19486189015023e-01 - 3.98423597346806e-02 -1.14207712398320e-01 - 3.56899752436130e-02 -1.08942873750492e-01 - 3.18292350050658e-02 -1.03766019819563e-01 - 2.82200072057899e-02 -9.83713136095624e-02 - 2.48925247792699e-02 -9.29813292559544e-02 - 2.18286683030034e-02 -8.75812750559987e-02 - 1.89846947131331e-02 -8.22315141653086e-02 - 1.63921917020335e-02 -7.68375469351822e-02 - 1.40446346341990e-02 -7.15805178400502e-02 - 1.18798249846349e-02 -6.63844826354807e-02 - 9.93094518736223e-03 -6.11819014551945e-02 - 8.21940795734749e-03 -5.61598781483703e-02 - 6.65838622137879e-03 -5.08510773625986e-02 - 5.26774192850643e-03 -4.53572429422233e-02 - 4.09515753852961e-03 -3.97028226277835e-02 - 3.09878859713640e-03 -3.40946000065125e-02 - 2.19660773551101e-03 -2.74113415852710e-02 - 1.46264176301869e-03 -2.17195675186239e-02 - 9.64484608297914e-04 -1.69031637821185e-02 - 5.99373867982851e-04 -1.26321409905378e-02 - 2.90086645599082e-04 -6.87137137840380e-03 - 7.80707788302466e-05 -4.31820009412653e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.58212361329831e-03 - 2.89878724192004e-04 4.58058532623794e-03 - 5.98775316682048e-04 9.40600053500757e-03 - 9.63326351634835e-04 1.32615736177810e-02 - 1.45966821282819e-03 1.79240093684486e-02 - 2.19097636449990e-03 2.36819029987386e-02 - 3.08997841959778e-03 3.12277958483986e-02 - 4.08271112470316e-03 3.76706756936067e-02 - 5.24853124383664e-03 4.40955670806266e-02 - 6.63128223001261e-03 5.00494859716516e-02 - 8.18368429859057e-03 5.56275911450637e-02 - 9.88361416849065e-03 6.08057536058205e-02 - 1.18176401547236e-02 6.61550748925812e-02 - 1.39661993216829e-02 7.15259505366298e-02 - 1.62951420791042e-02 7.70005600532738e-02 - 1.88631937781153e-02 8.25512202780009e-02 - 2.16807137532775e-02 8.81211958227384e-02 - 2.47159162958630e-02 9.37981589313452e-02 - 2.80064400105862e-02 9.94382296943884e-02 - 3.15762558914965e-02 1.05043310273264e-01 - 3.53948396168776e-02 1.10611882806451e-01 - 3.94949825480075e-02 1.16172580235854e-01 - 4.38979282781582e-02 1.21785796343949e-01 - 4.85758075737765e-02 1.27283432214041e-01 - 5.35679916138119e-02 1.32714912307852e-01 - 5.88818211488708e-02 1.38143146634474e-01 - 6.45001629027312e-02 1.43484120425231e-01 - 7.04692046391145e-02 1.48748989977238e-01 - 7.67740309924711e-02 1.53887337320431e-01 - 8.34162127168367e-02 1.58900914354282e-01 - 9.04290195190654e-02 1.63785146510973e-01 - 9.77906533229447e-02 1.68491682766590e-01 - 1.05536187198748e-01 1.73124174790704e-01 - 1.13658760041779e-01 1.77493811505195e-01 - 1.22161483318940e-01 1.81787174021769e-01 - 1.31067498602735e-01 1.85859688767915e-01 - 1.40354649921884e-01 1.89745616698670e-01 - 1.50055110786138e-01 1.93393383766123e-01 - 1.60148962661562e-01 1.96818342535027e-01 - 1.70658187899640e-01 2.00012125429582e-01 - 1.81574957422924e-01 2.02933425869279e-01 - 1.92907571409635e-01 2.05563652259819e-01 - 2.04657634577812e-01 2.07859983749229e-01 - 2.16817353069425e-01 2.09849120299579e-01 - 2.29396483963478e-01 2.11538027763547e-01 - 2.42377800694080e-01 2.12905548847383e-01 - 2.55773624268338e-01 2.13934712345069e-01 - 2.69566785632899e-01 2.14639888510867e-01 - 2.83765797226135e-01 2.14953966751574e-01 - 2.98347982887804e-01 2.14981489086608e-01 - 3.13318978785268e-01 2.14616878702686e-01 - 3.28658461892810e-01 2.13863501440321e-01 - 3.44364941645546e-01 2.12705152460777e-01 - 3.60419773725681e-01 2.11302859893205e-01 - 3.76811233766957e-01 2.09386818312783e-01 - 3.93525251020729e-01 2.07198182528411e-01 - 4.10538642553571e-01 2.04619874431247e-01 - 4.27843232490823e-01 2.01706635601237e-01 - 4.45406663468198e-01 1.98399719112213e-01 - 4.63222254103030e-01 1.94783017281374e-01 - 4.81251545655716e-01 1.90848855121115e-01 - 4.99481026671737e-01 1.86570225697046e-01 - 5.17879583085697e-01 1.82012870817386e-01 - 5.36417631367010e-01 1.77138738598319e-01 - 5.55075704909560e-01 1.72021163655966e-01 - 5.73808427242608e-01 1.66739758718032e-01 - 5.92596731105059e-01 1.61170409836523e-01 - 6.11401377553511e-01 1.55499091503200e-01 - 6.30186430605241e-01 1.49664722291398e-01 - 6.48926781663159e-01 1.43636596741773e-01 - 6.67570206424973e-01 1.37575421046107e-01 - 6.86088429590952e-01 1.31397864588368e-01 - 7.04445389043917e-01 1.25101099004796e-01 - 7.22592093722966e-01 1.18832802620711e-01 - 7.40501800453524e-01 1.12546614249516e-01 - 7.58125457122835e-01 1.06250223390604e-01 - 7.75421014376153e-01 1.00010799990375e-01 - 7.92362373587600e-01 9.37667267609895e-02 - 8.08894546151696e-01 8.76448515262541e-02 - 8.24974633014891e-01 8.16339359961337e-02 - 8.40576952273409e-01 7.57633989603419e-02 - 8.55652758808818e-01 6.99729060577023e-02 - 8.70162898882712e-01 6.43911931753109e-02 - 8.84085033071272e-01 5.89940803412250e-02 - 8.97361214262371e-01 5.38896610159258e-02 - 9.09954680076662e-01 4.89555478580711e-02 - 9.21851471402547e-01 4.43118444102265e-02 - 9.33012836658427e-01 3.99435082575581e-02 - 9.43389278969050e-01 3.58813032430998e-02 - 9.52973153850560e-01 3.20064712994813e-02 - 9.61743130827061e-01 2.84230423019687e-02 - 9.69640690675464e-01 2.51627205320165e-02 - 9.76664215898664e-01 2.22329472992652e-02 - 9.82815077112014e-01 1.96306821838321e-02 - 9.88028440045103e-01 1.73753463368503e-02 - 9.92304836603751e-01 1.54211547525815e-02 - 9.95693518775914e-01 1.38234835720738e-02 - 9.98120489340015e-01 1.26908076227732e-02 - 9.99443037908705e-01 1.21304050615068e-02 - 1.00000000000000e+00 1.21271186250935e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_10.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_10.dat index acdb11fb..8d246a14 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_10.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_10.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_10_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF10_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF10_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.158085 alpha0 ! 0-lift angle of attack, depends on airfoil. - 11.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -11.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-10.481203 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.581754 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.723097 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.941545 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.242936 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.025856 Cd0 ! 2D drag coefficient value at 0-lift. - -0.080375 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.028135 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079152 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -1.12089399712588e-03 4.73946801627918e-02 4.38986504672921e-03 --1.77714285740401e+02 7.56187749662004e-02 4.56412979994970e-02 9.42218522338173e-02 --1.75428571400002e+02 1.54052847598099e-01 4.86453102790644e-02 1.85888402702244e-01 --1.73142857116900e+02 2.35117294866798e-01 5.29791881138035e-02 2.74496366617252e-01 --1.70857160423602e+02 3.17577697098120e-01 5.64775372581035e-02 3.58293843606042e-01 --1.68571631778825e+02 4.00233156474893e-01 5.95169493946578e-02 3.91549522755184e-01 --1.66285714267592e+02 4.81911878875419e-01 6.68925327053549e-02 3.94790187149012e-01 --1.63999999984490e+02 5.61399315653268e-01 8.67622113981421e-02 3.96866181985072e-01 --1.61714472886699e+02 6.37499641349918e-01 1.14601335117924e-01 4.00554938103146e-01 --1.59428371284127e+02 7.09335510102079e-01 1.45544718661443e-01 4.05749359001752e-01 --1.57142842639350e+02 7.77115353826116e-01 1.80337499760308e-01 4.19649660044009e-01 --1.54857313994574e+02 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0.00000000000000e+00 4.85365970495091e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_10_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_10_Coords.txt deleted file mode 100644 index 53009c2d..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_10_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.338450 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -2.33488524413955e-03 - 9.99429683992583e-01 -2.04622618498614e-03 - 9.98063017832965e-01 -2.11439225272557e-03 - 9.95573914266674e-01 -2.31809103805826e-03 - 9.92086309749559e-01 -2.57931111018970e-03 - 9.87686148675057e-01 -2.87865078258838e-03 - 9.82330525170640e-01 -3.21293392029366e-03 - 9.76011908335692e-01 -3.58356856512312e-03 - 9.68787467298381e-01 -3.99222562192393e-03 - 9.60674860259240e-01 -4.44098000045110e-03 - 9.51675358763677e-01 -5.86532669682802e-03 - 9.41827652746244e-01 -7.14664260021431e-03 - 9.31175295355131e-01 -8.35811225532140e-03 - 9.19730397431178e-01 -1.01408399054897e-02 - 9.07524559194720e-01 -1.11546744153606e-02 - 8.94610408070308e-01 -1.27014773584062e-02 - 8.81009696499435e-01 -1.48100464557916e-02 - 8.66747905197194e-01 -1.75504785294015e-02 - 8.51890258171205e-01 -2.09204311957635e-02 - 8.36469462621421e-01 -2.49784207455253e-02 - 8.20513485943698e-01 -2.96925010412606e-02 - 8.04073832217581e-01 -3.49982384532901e-02 - 7.87191529885653e-01 -4.09313573922751e-02 - 7.69897919101553e-01 -4.73973945249429e-02 - 7.52252341235159e-01 -5.43775134008093e-02 - 7.34291349178558e-01 -6.18843643807502e-02 - 7.16044924955764e-01 -6.98241546913691e-02 - 6.97571640033109e-01 -7.80592876592211e-02 - 6.78906186433687e-01 -8.65027733520166e-02 - 6.60080312620540e-01 -9.50872806802620e-02 - 6.41147517137212e-01 -1.03654028787616e-01 - 6.22137650968852e-01 -1.12135165536821e-01 - 6.03087998194415e-01 -1.20444763948051e-01 - 5.84045042118975e-01 -1.28480686726064e-01 - 5.65030897687003e-01 -1.36240154334785e-01 - 5.46088602779599e-01 -1.43661059381893e-01 - 5.27248673916899e-01 -1.50663638653502e-01 - 5.08535950506088e-01 -1.57246707508831e-01 - 4.89992355470388e-01 -1.63404079517865e-01 - 4.71632114506831e-01 -1.69052406021233e-01 - 4.53492503744347e-01 -1.74245209375789e-01 - 4.35593302897673e-01 -1.78879462796109e-01 - 4.17956065616942e-01 -1.82941994661855e-01 - 4.00609748442576e-01 -1.86448345612289e-01 - 3.83560931606009e-01 -1.89431649911975e-01 - 3.66843215733716e-01 -1.91884084382417e-01 - 3.50457316320503e-01 -1.93826692842459e-01 - 3.34434484008630e-01 -1.95324879324069e-01 - 3.18774100329315e-01 -1.96315796413688e-01 - 3.03499623121295e-01 -1.96886599813150e-01 - 2.88611293565648e-01 -1.97040114236265e-01 - 2.74124386665666e-01 -1.96796665447177e-01 - 2.60041455523719e-01 -1.96139771036979e-01 - 2.46374872015917e-01 -1.95138478897237e-01 - 2.33123443938834e-01 -1.93765854815522e-01 - 2.20293777810423e-01 -1.92110970609977e-01 - 2.07883282965331e-01 -1.90138056613438e-01 - 1.95902956391646e-01 -1.87890288893168e-01 - 1.84341253066628e-01 -1.85405128790966e-01 - 1.73213930954160e-01 -1.82650003782803e-01 - 1.62499176129638e-01 -1.79733518384497e-01 - 1.52214602777260e-01 -1.76573802120820e-01 - 1.42331759398971e-01 -1.73232563913887e-01 - 1.32872111539190e-01 -1.69722930588454e-01 - 1.23806439629760e-01 -1.66036630682668e-01 - 1.15147623386077e-01 -1.62188720729215e-01 - 1.06887208802748e-01 -1.58249033597289e-01 - 9.90071115215634e-02 -1.54142372782377e-01 - 9.15234043853439e-02 -1.49948066372342e-01 - 8.43970428172224e-02 -1.45613742882988e-01 - 7.76464790199521e-02 -1.41170910446556e-01 - 7.12479082120209e-02 -1.36643243512138e-01 - 6.51878662973747e-02 -1.31984164078647e-01 - 5.94874721274202e-02 -1.27273907593862e-01 - 5.41002464180900e-02 -1.22493972125796e-01 - 4.90378786701877e-02 -1.17657995672869e-01 - 4.43003497573338e-02 -1.12821192207831e-01 - 3.98423597346806e-02 -1.07875267763411e-01 - 3.56899752436130e-02 -1.02931258190856e-01 - 3.18292350050658e-02 -9.80244445848123e-02 - 2.82200072057899e-02 -9.29738951282296e-02 - 2.48925247792699e-02 -8.79180023538076e-02 - 2.18286683030034e-02 -8.28451481869776e-02 - 1.89846947131331e-02 -7.77548000385951e-02 - 1.63921917020335e-02 -7.26495325379647e-02 - 1.40446346341990e-02 -6.76670372738446e-02 - 1.18798249846349e-02 -6.27124767871754e-02 - 9.93094518736223e-03 -5.78027117417994e-02 - 8.21940795734749e-03 -5.30851086453997e-02 - 6.65838622137879e-03 -4.81128181117354e-02 - 5.26774192850643e-03 -4.29884634424200e-02 - 4.09515753852961e-03 -3.77191723066699e-02 - 3.09878859713640e-03 -3.22714075274508e-02 - 2.19660773551101e-03 -2.59349591310743e-02 - 1.46264176301869e-03 -2.04391634415134e-02 - 9.64484608297914e-04 -1.58198506340899e-02 - 5.99373867982851e-04 -1.15393216780958e-02 - 2.90086645599082e-04 -5.80639160447645e-03 - 7.80707788302466e-05 -2.80063795917175e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.31550035014314e-03 - 2.89878724192004e-04 4.41778901022517e-03 - 5.98775316682048e-04 8.90179091248226e-03 - 9.63326351634835e-04 1.27865340182651e-02 - 1.45966821282819e-03 1.72063667890173e-02 - 2.19097636449990e-03 2.28221754884265e-02 - 3.08997841959778e-03 3.01149814075584e-02 - 4.08271112470316e-03 3.65199834083942e-02 - 5.24853124383664e-03 4.25316531148704e-02 - 6.63128223001261e-03 4.81517752567604e-02 - 8.18368429859057e-03 5.33733501051875e-02 - 9.88361416849065e-03 5.82447038895505e-02 - 1.18176401547236e-02 6.33454516186426e-02 - 1.39661993216829e-02 6.84882179489016e-02 - 1.62951420791042e-02 7.37064108755996e-02 - 1.88631937781153e-02 7.90156700468861e-02 - 2.16807137532775e-02 8.43452366657605e-02 - 2.47159162958630e-02 8.97074115055119e-02 - 2.80064400105862e-02 9.50530406338864e-02 - 3.15762558914965e-02 1.00387008556298e-01 - 3.53948396168776e-02 1.05680403135004e-01 - 3.94949825480075e-02 1.10960463962679e-01 - 4.38979282781582e-02 1.16266777233463e-01 - 4.85758075737765e-02 1.21476861417524e-01 - 5.35679916138119e-02 1.26627045385719e-01 - 5.88818211488708e-02 1.31746304386520e-01 - 6.45001629027312e-02 1.36772419289008e-01 - 7.04692046391145e-02 1.41711608359124e-01 - 7.67740309924711e-02 1.46528740217678e-01 - 8.34162127168367e-02 1.51222510127765e-01 - 9.04290195190654e-02 1.55797955158041e-01 - 9.77906533229447e-02 1.60197654090740e-01 - 1.05536187198748e-01 1.64481697092519e-01 - 1.13658760041779e-01 1.68549725284276e-01 - 1.22161483318940e-01 1.72495965629610e-01 - 1.31067498602735e-01 1.76238253358814e-01 - 1.40354649921884e-01 1.79781447474656e-01 - 1.50055110786138e-01 1.83089708793626e-01 - 1.60148962661562e-01 1.86158630919829e-01 - 1.70658187899640e-01 1.88984267336680e-01 - 1.81574957422924e-01 1.91536789486217e-01 - 1.92907571409635e-01 1.93798091308764e-01 - 2.04657634577812e-01 1.95744046111998e-01 - 2.16817353069425e-01 1.97377249578857e-01 - 2.29396483963478e-01 1.98711596225308e-01 - 2.42377800694080e-01 1.99722853747060e-01 - 2.55773624268338e-01 2.00409550719760e-01 - 2.69566785632899e-01 2.00764627956102e-01 - 2.83765797226135e-01 2.00769533959330e-01 - 2.98347982887804e-01 2.00466901130711e-01 - 3.13318978785268e-01 1.99804911555774e-01 - 3.28658461892810e-01 1.98776828789932e-01 - 3.44364941645546e-01 1.97377254330031e-01 - 3.60419773725681e-01 1.95693317507381e-01 - 3.76811233766957e-01 1.93597536553932e-01 - 3.93525251020729e-01 1.91204199607715e-01 - 4.10538642553571e-01 1.88453264863488e-01 - 4.27843232490823e-01 1.85394225704471e-01 - 4.45406663468198e-01 1.81995624276020e-01 - 4.63222254103030e-01 1.78311386754930e-01 - 4.81251545655716e-01 1.74342236615250e-01 - 4.99481026671737e-01 1.70088834797476e-01 - 5.17879583085697e-01 1.65590062053805e-01 - 5.36417631367010e-01 1.60841712108104e-01 - 5.55075704909560e-01 1.55896647843216e-01 - 5.73808427242608e-01 1.50790958196048e-01 - 5.92596731105059e-01 1.45492029909440e-01 - 6.11401377553511e-01 1.40096020953641e-01 - 6.30186430605241e-01 1.34579755363622e-01 - 6.48926781663159e-01 1.28948148828841e-01 - 6.67570206424973e-01 1.23296016934627e-01 - 6.86088429590952e-01 1.17582386901190e-01 - 7.04445389043917e-01 1.11818587320324e-01 - 7.22592093722966e-01 1.06090225392703e-01 - 7.40501800453524e-01 1.00368427789368e-01 - 7.58125457122835e-01 9.46878815152301e-02 - 7.75421014376153e-01 8.90734556812336e-02 - 7.92362373587600e-01 8.35071243301492e-02 - 8.08894546151696e-01 7.80558414264322e-02 - 8.24974633014891e-01 7.27319756870650e-02 - 8.40576952273409e-01 6.75481046520951e-02 - 8.55652758808818e-01 6.24860536513426e-02 - 8.70162898882712e-01 5.76177192117095e-02 - 8.84085033071272e-01 5.29233239253907e-02 - 8.97361214262371e-01 4.84681180016263e-02 - 9.09954680076662e-01 4.42075305243365e-02 - 9.21851471402547e-01 4.02047366400575e-02 - 9.33012836658427e-01 3.64480227181224e-02 - 9.43389278969050e-01 3.29422664376505e-02 - 9.52973153850560e-01 2.96196496670599e-02 - 9.61743130827061e-01 2.65501872946556e-02 - 9.69640690675464e-01 2.37607337114641e-02 - 9.76664215898664e-01 2.12559054067185e-02 - 9.82815077112014e-01 1.90282278512964e-02 - 9.88028440045103e-01 1.70875307250985e-02 - 9.92304836603751e-01 1.53779898120962e-02 - 9.95693518775914e-01 1.40889377545732e-02 - 9.98120489340015e-01 1.32115618238902e-02 - 9.99443037908705e-01 1.28246140796479e-02 - 1.00000000000000e+00 1.26721021367096e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_11.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_11.dat index cd9fcb42..46bda5a8 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_11.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_11.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_11_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF11_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF11_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.111714 alpha0 ! 0-lift angle of attack, depends on airfoil. - 11.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -11.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-10.125254 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.571166 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.729386 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.942328 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.253626 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.017705 Cd0 ! 2D drag coefficient value at 0-lift. - -0.080840 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.018852 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079875 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 2.53946984581007e-03 4.09745974305007e-02 4.81521958477874e-03 --1.77714285740401e+02 7.29930143869915e-02 4.01393684364411e-02 9.20302982228442e-02 --1.75428571400002e+02 1.48041133583377e-01 4.27669389383983e-02 1.83188694045007e-01 --1.73142857116900e+02 2.22469264655344e-01 4.66366121327802e-02 2.74734282770831e-01 --1.70857160423602e+02 2.96419020839209e-01 5.03786538723746e-02 3.63869201278460e-01 --1.68571631778825e+02 3.70050620507924e-01 5.45661803223277e-02 4.01373483081450e-01 --1.66285714267592e+02 4.43549198486602e-01 6.40921502568840e-02 4.06027134486463e-01 --1.63999999984490e+02 5.17062116633674e-01 8.54919563103662e-02 4.09777820252592e-01 --1.61714472886699e+02 5.90753962703448e-01 1.14734302817313e-01 4.15455266375788e-01 --1.59428371284127e+02 6.64701283644103e-01 1.47691977821872e-01 4.22561689128519e-01 --1.57142842639350e+02 7.38449233350829e-01 1.83747868690147e-01 4.39520491547432e-01 --1.54857313994574e+02 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0.00000000000000e+00 4.12273098810148e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_11_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_11_Coords.txt deleted file mode 100644 index 16191aa3..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_11_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.330367 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -9.93661132028158e-04 - 9.99429683992583e-01 -9.37509043887931e-04 - 9.98063017832965e-01 -1.19300108398926e-03 - 9.95573914266674e-01 -1.47449765011736e-03 - 9.92086309749559e-01 -1.76678588846223e-03 - 9.87686148675057e-01 -2.06600575919516e-03 - 9.82330525170640e-01 -2.37140009691884e-03 - 9.76011908335692e-01 -2.68310718419518e-03 - 9.68787467298381e-01 -3.00136454367383e-03 - 9.60674860259240e-01 -3.32651023072001e-03 - 9.51675358763677e-01 -4.21685121824053e-03 - 9.41827652746244e-01 -5.00546199951502e-03 - 9.31175295355131e-01 -5.70360145807676e-03 - 9.19730397431178e-01 -6.94147879111550e-03 - 9.07524559194720e-01 -7.42924037497186e-03 - 8.94610408070308e-01 -8.41389850858184e-03 - 8.81009696499435e-01 -9.92316070080154e-03 - 8.66747905197194e-01 -1.20304061513551e-02 - 8.51890258171205e-01 -1.47508316540576e-02 - 8.36469462621421e-01 -1.81350547335999e-02 - 8.20513485943698e-01 -2.21682379481409e-02 - 8.04073832217581e-01 -2.68054819351273e-02 - 7.87191529885653e-01 -3.20521847735095e-02 - 7.69897919101553e-01 -3.78642885791239e-02 - 7.52252341235159e-01 -4.42391769602115e-02 - 7.34291349178558e-01 -5.11687933635027e-02 - 7.16044924955764e-01 -5.85775672662101e-02 - 6.97571640033109e-01 -6.63505758953099e-02 - 6.78906186433687e-01 -7.44116427494729e-02 - 6.60080312620540e-01 -8.26555232485203e-02 - 6.41147517137212e-01 -9.09641988380393e-02 - 6.22137650968852e-01 -9.92477168801398e-02 - 6.03087998194415e-01 -1.07417518171906e-01 - 5.84045042118975e-01 -1.15369343503955e-01 - 5.65030897687003e-01 -1.23077069368621e-01 - 5.46088602779599e-01 -1.30477753803581e-01 - 5.27248673916899e-01 -1.37504404541953e-01 - 5.08535950506088e-01 -1.44139705237019e-01 - 4.89992355470388e-01 -1.50354701678671e-01 - 4.71632114506831e-01 -1.56109186033898e-01 - 4.53492503744347e-01 -1.61394851348947e-01 - 4.35593302897673e-01 -1.66161056606926e-01 - 4.17956065616942e-01 -1.70366213540819e-01 - 4.00609748442576e-01 -1.74018254787761e-01 - 3.83560931606009e-01 -1.77145684814192e-01 - 3.66843215733716e-01 -1.79758437770771e-01 - 3.50457316320503e-01 -1.81876833847116e-01 - 3.34434484008630e-01 -1.83526672004626e-01 - 3.18774100329315e-01 -1.84705401929299e-01 - 3.03499623121295e-01 -1.85454311289432e-01 - 2.88611293565648e-01 -1.85788534240281e-01 - 2.74124386665666e-01 -1.85704527412483e-01 - 2.60041455523719e-01 -1.85245681426884e-01 - 2.46374872015917e-01 -1.84420980899029e-01 - 2.33123443938834e-01 -1.83244730428135e-01 - 2.20293777810423e-01 -1.81759180016114e-01 - 2.07883282965331e-01 -1.79969041259989e-01 - 1.95902956391646e-01 -1.77907621641427e-01 - 1.84341253066628e-01 -1.75596909301859e-01 - 1.73213930954160e-01 -1.73041150834219e-01 - 1.62499176129638e-01 -1.70296760316263e-01 - 1.52214602777260e-01 -1.67332273066250e-01 - 1.42331759398971e-01 -1.64175390192158e-01 - 1.32872111539190e-01 -1.60851911397039e-01 - 1.23806439629760e-01 -1.57356768741610e-01 - 1.15147623386077e-01 -1.53712902620115e-01 - 1.06887208802748e-01 -1.49959793115455e-01 - 9.90071115215634e-02 -1.46066589171407e-01 - 9.15234043853439e-02 -1.42074938340165e-01 - 8.43970428172224e-02 -1.37957767131317e-01 - 7.76464790199521e-02 -1.33738832143333e-01 - 7.12479082120209e-02 -1.29428103458620e-01 - 6.51878662973747e-02 -1.25009151963918e-01 - 5.94874721274202e-02 -1.20529752154749e-01 - 5.41002464180900e-02 -1.15975037111453e-01 - 4.90378786701877e-02 -1.11369141899695e-01 - 4.43003497573338e-02 -1.06745041585631e-01 - 3.98423597346806e-02 -1.02057182826122e-01 - 3.56899752436130e-02 -9.73662665507223e-02 - 3.18292350050658e-02 -9.26798609779526e-02 - 2.82200072057899e-02 -8.79070439929843e-02 - 2.48925247792699e-02 -8.31262247055993e-02 - 2.18286683030034e-02 -7.83288551193270e-02 - 1.89846947131331e-02 -7.34719782254969e-02 - 1.63921917020335e-02 -6.86263415829242e-02 - 1.40446346341990e-02 -6.38937004113913e-02 - 1.18798249846349e-02 -5.91643607235876e-02 - 9.93094518736223e-03 -5.45175777252172e-02 - 8.21940795734749e-03 -5.00652353271309e-02 - 6.65838622137879e-03 -4.53914728953444e-02 - 5.26774192850643e-03 -4.05962237353991e-02 - 4.09515753852961e-03 -3.56833504776259e-02 - 3.09878859713640e-03 -3.04308068802501e-02 - 2.19660773551101e-03 -2.44521763018762e-02 - 1.46264176301869e-03 -1.91812215160615e-02 - 9.64484608297914e-04 -1.48103974377391e-02 - 5.99373867982851e-04 -1.06542605648706e-02 - 2.90086645599082e-04 -5.18084994524396e-03 - 7.80707788302466e-05 -1.75465000530641e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.19089743437724e-03 - 2.89878724192004e-04 4.34512224294146e-03 - 5.98775316682048e-04 8.66823734989363e-03 - 9.63326351634835e-04 1.25696774983381e-02 - 1.45966821282819e-03 1.67701200334271e-02 - 2.19097636449990e-03 2.21076369100619e-02 - 3.08997841959778e-03 2.90150113567165e-02 - 4.08271112470316e-03 3.52848907332755e-02 - 5.24853124383664e-03 4.09038105427911e-02 - 6.63128223001261e-03 4.62113035174298e-02 - 8.18368429859057e-03 5.11176122446528e-02 - 9.88361416849065e-03 5.57212898961565e-02 - 1.18176401547236e-02 6.05860997997907e-02 - 1.39661993216829e-02 6.55095869348206e-02 - 1.62951420791042e-02 7.04839618783079e-02 - 1.88631937781153e-02 7.55603636737338e-02 - 2.16807137532775e-02 8.06615354223586e-02 - 2.47159162958630e-02 8.57432514930635e-02 - 2.80064400105862e-02 9.08265934269429e-02 - 3.15762558914965e-02 9.59177502002593e-02 - 3.53948396168776e-02 1.00967243885443e-01 - 3.94949825480075e-02 1.06001302197998e-01 - 4.38979282781582e-02 1.11044359506653e-01 - 4.85758075737765e-02 1.16008834114188e-01 - 5.35679916138119e-02 1.20920166611143e-01 - 5.88818211488708e-02 1.25784695166314e-01 - 6.45001629027312e-02 1.30554888630930e-01 - 7.04692046391145e-02 1.35235058749260e-01 - 7.67740309924711e-02 1.39800351176837e-01 - 8.34162127168367e-02 1.44246012992691e-01 - 9.04290195190654e-02 1.48582532824311e-01 - 9.77906533229447e-02 1.52750118901093e-01 - 1.05536187198748e-01 1.56777765724161e-01 - 1.13658760041779e-01 1.60624489612349e-01 - 1.22161483318940e-01 1.64319158498490e-01 - 1.31067498602735e-01 1.67824205144589e-01 - 1.40354649921884e-01 1.71125622344751e-01 - 1.50055110786138e-01 1.74198842396754e-01 - 1.60148962661562e-01 1.77027011856509e-01 - 1.70658187899640e-01 1.79605548694113e-01 - 1.81574957422924e-01 1.81915249308765e-01 - 1.92907571409635e-01 1.83938739778892e-01 - 2.04657634577812e-01 1.85660650367689e-01 - 2.16817353069425e-01 1.87073065216306e-01 - 2.29396483963478e-01 1.88188653473324e-01 - 2.42377800694080e-01 1.88987111303191e-01 - 2.55773624268338e-01 1.89472101417067e-01 - 2.69566785632899e-01 1.89627051945447e-01 - 2.83765797226135e-01 1.89460689386614e-01 - 2.98347982887804e-01 1.88976995318420e-01 - 3.13318978785268e-01 1.88159269149189e-01 - 3.28658461892810e-01 1.86997914360729e-01 - 3.44364941645546e-01 1.85491417214637e-01 - 3.60419773725681e-01 1.83682109597956e-01 - 3.76811233766957e-01 1.81526600866698e-01 - 3.93525251020729e-01 1.79064786557072e-01 - 4.10538642553571e-01 1.76274155718923e-01 - 4.27843232490823e-01 1.73193985596083e-01 - 4.45406663468198e-01 1.69813593160776e-01 - 4.63222254103030e-01 1.66166456582232e-01 - 4.81251545655716e-01 1.62257748488384e-01 - 4.99481026671737e-01 1.58104633483821e-01 - 5.17879583085697e-01 1.53732593728063e-01 - 5.36417631367010e-01 1.49154589864944e-01 - 5.55075704909560e-01 1.44408435309414e-01 - 5.73808427242608e-01 1.39509210183163e-01 - 5.92596731105059e-01 1.34469808633821e-01 - 6.11401377553511e-01 1.29336247541558e-01 - 6.30186430605241e-01 1.24106831929597e-01 - 6.48926781663159e-01 1.18804745087011e-01 - 6.67570206424973e-01 1.13483010129962e-01 - 6.86088429590952e-01 1.08128860083445e-01 - 7.04445389043917e-01 1.02759713012501e-01 - 7.22592093722966e-01 9.74236791374609e-02 - 7.40501800453524e-01 9.21059134949503e-02 - 7.58125457122835e-01 8.68520111537756e-02 - 7.75421014376153e-01 8.16672329571592e-02 - 7.92362373587600e-01 7.65579621191817e-02 - 8.08894546151696e-01 7.15589856198663e-02 - 8.24974633014891e-01 6.66892009339087e-02 - 8.40576952273409e-01 6.19571786129483e-02 - 8.55652758808818e-01 5.73702318344080e-02 - 8.70162898882712e-01 5.29644156448937e-02 - 8.84085033071272e-01 4.87282545731905e-02 - 8.97361214262371e-01 4.46985731930546e-02 - 9.09954680076662e-01 4.08746304724913e-02 - 9.21851471402547e-01 3.72864315446177e-02 - 9.33012836658427e-01 3.39284554470767e-02 - 9.43389278969050e-01 3.07930563721062e-02 - 9.52973153850560e-01 2.78419088443140e-02 - 9.61743130827061e-01 2.51211429507568e-02 - 9.69640690675464e-01 2.26528255632831e-02 - 9.76664215898664e-01 2.04401626378357e-02 - 9.82815077112014e-01 1.84789049998962e-02 - 9.88028440045103e-01 1.67819981423078e-02 - 9.92304836603751e-01 1.53164788288186e-02 - 9.95693518775914e-01 1.42250570339080e-02 - 9.98120489340015e-01 1.34785935425061e-02 - 9.99443037908705e-01 1.31805897526145e-02 - 1.00000000000000e+00 1.29267638225190e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_12.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_12.dat index 721ed5d2..4a62b3b9 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_12.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_12.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_12_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF12_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF12_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.075816 alpha0 ! 0-lift angle of attack, depends on airfoil. - 11.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -11.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-9.912430 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.568133 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.736254 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.941291 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.266353 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.014881 Cd0 ! 2D drag coefficient value at 0-lift. - -0.081293 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.015893 Cd0 ! 2D drag coefficient value at 0-lift. +-0.080551 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 3.34090681674207e-03 3.73112893830816e-02 4.90737037868525e-03 --1.77714285740401e+02 7.17996155690199e-02 3.78707932838646e-02 9.15110590051832e-02 --1.75428571400002e+02 1.45380361386304e-01 3.96469900190143e-02 1.82597592607693e-01 --1.73142857116900e+02 2.17154766460144e-01 4.23646402837618e-02 2.74781606651763e-01 --1.70857160423602e+02 2.87778719113613e-01 4.59933878655969e-02 3.65105641046615e-01 --1.68571631778825e+02 3.57904035783051e-01 5.14219271000549e-02 4.03474402591060e-01 --1.66285714267592e+02 4.28204220489919e-01 6.32198558086919e-02 4.08396850739218e-01 --1.63999999984490e+02 4.99317542113772e-01 8.52346952100428e-02 4.12509768029502e-01 --1.61714472886699e+02 5.71900637960087e-01 1.14763416106265e-01 4.18618353911624e-01 --1.59428371284127e+02 6.46318913684429e-01 1.48162120395448e-01 4.26139923486004e-01 --1.57142842639350e+02 7.21613487254221e-01 1.84494569253853e-01 4.43762961634483e-01 --1.54857313994574e+02 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0.00000000000000e+00 3.71823486494224e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_12_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_12_Coords.txt deleted file mode 100644 index 47e6dd59..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_12_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.324012 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -7.00000000000000e-04 - 9.99429683992583e-01 -7.00000000000000e-04 - 9.98063017832965e-01 -1.00000034701682e-03 - 9.95573914266674e-01 -1.29999956764765e-03 - 9.92086309749559e-01 -1.60000001913569e-03 - 9.87686148675057e-01 -1.90000008174800e-03 - 9.82330525170640e-01 -2.20000024877022e-03 - 9.76011908335692e-01 -2.50000007384419e-03 - 9.68787467298381e-01 -2.80000010580820e-03 - 9.60674860259240e-01 -3.09999999090215e-03 - 9.51675358763677e-01 -3.40000003938487e-03 - 9.41827652746244e-01 -3.69999991958105e-03 - 9.31175295355131e-01 -4.00000018499118e-03 - 9.19730397431178e-01 -4.79161007928258e-03 - 9.07524559194720e-01 -5.03220002331829e-03 - 8.94610408070308e-01 -5.74853013213580e-03 - 8.81009696499435e-01 -6.97163036693134e-03 - 8.66747905197194e-01 -8.76892067871256e-03 - 8.51890258171205e-01 -1.11631003238711e-02 - 8.36469462621421e-01 -1.41983094445431e-02 - 8.20513485943698e-01 -1.78629609885987e-02 - 8.04073832217581e-01 -2.21334093939271e-02 - 7.87191529885653e-01 -2.70034800344577e-02 - 7.69897919101553e-01 -3.24602702949463e-02 - 7.52252341235159e-01 -3.84986195623356e-02 - 7.34291349178558e-01 -4.50983403103173e-02 - 7.16044924955764e-01 -5.21916580332444e-02 - 6.97571640033109e-01 -5.96798899863621e-02 - 6.78906186433687e-01 -6.74951915064082e-02 - 6.60080312620540e-01 -7.55182388790160e-02 - 6.41147517137212e-01 -8.36476112274016e-02 - 6.22137650968852e-01 -9.17858795877241e-02 - 6.03087998194415e-01 -9.98435407553425e-02 - 5.84045042118975e-01 -1.07723379135459e-01 - 5.65030897687003e-01 -1.15374090914418e-01 - 5.46088602779599e-01 -1.22734278943791e-01 - 5.27248673916899e-01 -1.29738928579581e-01 - 5.08535950506088e-01 -1.36362089825903e-01 - 4.89992355470388e-01 -1.42567551467097e-01 - 4.71632114506831e-01 -1.48329738637820e-01 - 4.53492503744347e-01 -1.53617848955891e-01 - 4.35593302897673e-01 -1.58401969267069e-01 - 4.17956065616942e-01 -1.62636940988611e-01 - 4.00609748442576e-01 -1.66326900308995e-01 - 3.83560931606009e-01 -1.69497199724448e-01 - 3.66843215733716e-01 -1.72160930618164e-01 - 3.50457316320503e-01 -1.74339080434707e-01 - 3.34434484008630e-01 -1.76043859634536e-01 - 3.18774100329315e-01 -1.77294039978911e-01 - 3.03499623121295e-01 -1.78111789887102e-01 - 2.88611293565648e-01 -1.78519250000000e-01 - 2.74124386665666e-01 -1.78504039993234e-01 - 2.60041455523719e-01 -1.78128929839406e-01 - 2.46374872015917e-01 -1.77382100132364e-01 - 2.33123443938834e-01 -1.76295210369824e-01 - 2.20293777810423e-01 -1.74889309732930e-01 - 2.07883282965331e-01 -1.73184950444320e-01 - 1.95902956391646e-01 -1.71212299359069e-01 - 1.84341253066628e-01 -1.68985360631511e-01 - 1.73213930954160e-01 -1.66526040223253e-01 - 1.62499176129638e-01 -1.63864898982321e-01 - 1.52214602777260e-01 -1.60994440816281e-01 - 1.42331759398971e-01 -1.57929179804538e-01 - 1.32872111539190e-01 -1.54698240550305e-01 - 1.23806439629760e-01 -1.51300269855196e-01 - 1.15147623386077e-01 -1.47762281439195e-01 - 1.06887208802748e-01 -1.44106589448613e-01 - 9.90071115215634e-02 -1.40326190758737e-01 - 9.15234043853439e-02 -1.36443932364723e-01 - 8.43970428172224e-02 -1.32445941642471e-01 - 7.76464790199521e-02 -1.28352669383037e-01 - 7.12479082120209e-02 -1.24167568785528e-01 - 6.51878662973747e-02 -1.19889627286666e-01 - 5.94874721274202e-02 -1.15550361679364e-01 - 5.41002464180900e-02 -1.11137496958766e-01 - 4.90378786701877e-02 -1.06679798786493e-01 - 4.43003497573338e-02 -1.02197359762367e-01 - 3.98423597346806e-02 -9.76768297211961e-02 - 3.56899752436130e-02 -9.31530946211419e-02 - 3.18292350050658e-02 -8.86187539000067e-02 - 2.82200072057899e-02 -8.40324863007659e-02 - 2.48925247792699e-02 -7.94401768808434e-02 - 2.18286683030034e-02 -7.48355673319120e-02 - 1.89846947131331e-02 -7.01533580993628e-02 - 1.63921917020335e-02 -6.55006431722660e-02 - 1.40446346341990e-02 -6.09558793511174e-02 - 1.18798249846349e-02 -5.64000309279292e-02 - 9.93094518736223e-03 -5.19480685230042e-02 - 8.21940795734749e-03 -4.76871245612724e-02 - 6.65838622137879e-03 -4.32303584549729e-02 - 5.26774192850643e-03 -3.86738069366256e-02 - 4.09515753852961e-03 -3.40269289896673e-02 - 3.09878859713640e-03 -2.89511720785438e-02 - 2.19660773551101e-03 -2.32598450360729e-02 - 1.46264176301869e-03 -1.81846233909941e-02 - 9.64484608297914e-04 -1.40419837600524e-02 - 5.99373867982851e-04 -1.00658711715362e-02 - 2.90086645599082e-04 -4.93019275712732e-03 - 7.80707788302466e-05 -1.22142275482833e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.16484801115279e-03 - 2.89878724192004e-04 4.33031159275536e-03 - 5.98775316682048e-04 8.61964315523606e-03 - 9.63326351634835e-04 1.25249160374163e-02 - 1.45966821282819e-03 1.65598465993927e-02 - 2.19097636449990e-03 2.15988443162193e-02 - 3.08997841959778e-03 2.81269394590481e-02 - 4.08271112470316e-03 3.42339159157158e-02 - 5.24853124383664e-03 3.95524550728874e-02 - 6.63128223001261e-03 4.46229573913631e-02 - 8.18368429859057e-03 4.93010519997975e-02 - 9.88361416849065e-03 5.37117704485055e-02 - 1.18176401547236e-02 5.83935403578952e-02 - 1.39661993216829e-02 6.31446885544247e-02 - 1.62951420791042e-02 6.79296841133127e-02 - 1.88631937781153e-02 7.28229168920636e-02 - 2.16807137532775e-02 7.77462162860205e-02 - 2.47159162958630e-02 8.26219942780693e-02 - 2.80064400105862e-02 8.75121500151331e-02 - 3.15762558914965e-02 9.24229445598229e-02 - 3.53948396168776e-02 9.72927195293445e-02 - 3.94949825480075e-02 1.02147172910745e-01 - 4.38979282781582e-02 1.07002198171150e-01 - 4.85758075737765e-02 1.11791187608345e-01 - 5.35679916138119e-02 1.16532401476867e-01 - 5.88818211488708e-02 1.21220980975675e-01 - 6.45001629027312e-02 1.25816762280485e-01 - 7.04692046391145e-02 1.30324283366185e-01 - 7.67740309924711e-02 1.34723850665528e-01 - 8.34162127168367e-02 1.39007821683963e-01 - 9.04290195190654e-02 1.43188599725771e-01 - 9.77906533229447e-02 1.47208291734702e-01 - 1.05536187198748e-01 1.51078758662581e-01 - 1.13658760041779e-01 1.54788810018214e-01 - 1.22161483318940e-01 1.58331731315381e-01 - 1.31067498602735e-01 1.61694579499659e-01 - 1.40354649921884e-01 1.64854629974951e-01 - 1.50055110786138e-01 1.67793530223250e-01 - 1.60148962661562e-01 1.70488890661966e-01 - 1.70658187899640e-01 1.72932769548363e-01 - 1.81574957422924e-01 1.75113789529699e-01 - 1.92907571409635e-01 1.77015280212619e-01 - 2.04657634577812e-01 1.78623110551244e-01 - 2.16817353069425e-01 1.79928860282386e-01 - 2.29396483963478e-01 1.80939680256632e-01 - 2.42377800694080e-01 1.81642300026593e-01 - 2.55773624268338e-01 1.82038560038307e-01 - 2.69566785632899e-01 1.82111230000000e-01 - 2.83765797226135e-01 1.81878350063353e-01 - 2.98347982887804e-01 1.81326909867823e-01 - 3.13318978785268e-01 1.80457100080829e-01 - 3.28658461892810e-01 1.79261239836413e-01 - 3.44364941645546e-01 1.77736969827586e-01 - 3.60419773725681e-01 1.75908089546424e-01 - 3.76811233766957e-01 1.73764189479591e-01 - 3.93525251020729e-01 1.71316549843026e-01 - 4.10538642553571e-01 1.68561129570034e-01 - 4.27843232490823e-01 1.65526389547381e-01 - 4.45406663468198e-01 1.62214479326513e-01 - 4.63222254103030e-01 1.58648069156013e-01 - 4.81251545655716e-01 1.54834000940157e-01 - 4.99481026671737e-01 1.50795720751788e-01 - 5.17879583085697e-01 1.46556249276545e-01 - 5.36417631367010e-01 1.42132359669226e-01 - 5.55075704909560e-01 1.37553638778952e-01 - 5.73808427242608e-01 1.32830940702902e-01 - 5.92596731105059e-01 1.27987549712573e-01 - 6.11401377553511e-01 1.23052120647977e-01 - 6.30186430605241e-01 1.18030769837096e-01 - 6.48926781663159e-01 1.12951579546985e-01 - 6.67570206424973e-01 1.07848020984119e-01 - 6.86088429590952e-01 1.02721810113781e-01 - 7.04445389043917e-01 9.75908202680647e-02 - 7.22592093722966e-01 9.24871289482642e-02 - 7.40501800453524e-01 8.74050998711276e-02 - 7.58125457122835e-01 8.23901908207147e-02 - 7.75421014376153e-01 7.74445987465071e-02 - 7.92362373587600e-01 7.25836689697121e-02 - 8.08894546151696e-01 6.78317911068638e-02 - 8.24974633014891e-01 6.32037191321439e-02 - 8.40576952273409e-01 5.87118293457399e-02 - 8.55652758808818e-01 5.43748403422260e-02 - 8.70162898882712e-01 5.02115003204906e-02 - 8.84085033071272e-01 4.62190691200949e-02 - 8.97361214262371e-01 4.24190687822866e-02 - 9.09954680076662e-01 3.88278799782239e-02 - 9.21851471402547e-01 3.54613896042300e-02 - 9.33012836658427e-01 3.23205209413468e-02 - 9.43389278969050e-01 2.93943302925962e-02 - 9.52973153850560e-01 2.66572088977387e-02 - 9.61743130827061e-01 2.41410397621092e-02 - 9.69640690675464e-01 2.18638598047294e-02 - 9.76664215898664e-01 1.98283211916885e-02 - 9.82815077112014e-01 1.80367208432355e-02 - 9.88028440045103e-01 1.65110299867720e-02 - 9.92304836603751e-01 1.52542809999372e-02 - 9.95693518775914e-01 1.42548603615542e-02 - 9.98120489340015e-01 1.35370601597314e-02 - 9.99443037908705e-01 1.32585306561174e-02 - 1.00000000000000e+00 1.29800000000000e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_13.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_13.dat index ecb4b30d..a9212dc8 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_13.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_13.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_13_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF13_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF13_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.011141 alpha0 ! 0-lift angle of attack, depends on airfoil. - 12.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -12.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-10.090819 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.624623 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.758946 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.953700 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.288390 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.013963 Cd0 ! 2D drag coefficient value at 0-lift. - -0.082398 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.015192 Cd0 ! 2D drag coefficient value at 0-lift. +-0.081549 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 3.33621861424975e-03 3.53331111261055e-02 4.89388871143273e-03 --1.77714285740401e+02 7.13047545834612e-02 3.70523242013988e-02 9.14750324681289e-02 --1.75428571400002e+02 1.44312953494847e-01 3.81089347300521e-02 1.82652815684701e-01 --1.73142857116900e+02 2.15151639729507e-01 3.94500431157865e-02 2.74704126408508e-01 --1.70857160423602e+02 2.84634292601253e-01 4.26011982956711e-02 3.65176706104961e-01 --1.68571631778825e+02 3.53563218085402e-01 4.93778878276042e-02 4.03506783353719e-01 --1.66285714267592e+02 4.22761705979200e-01 6.30101186865469e-02 4.08363037767010e-01 --1.63999999984490e+02 4.93018744697283e-01 8.52981078122034e-02 4.12485673826543e-01 --1.61714472886699e+02 5.65141942824817e-01 1.14361000894255e-01 4.18600212155057e-01 --1.59428371284127e+02 6.39549013374409e-01 1.47337065703936e-01 4.26076488980749e-01 --1.57142842639350e+02 7.14948645666727e-01 1.83411819574100e-01 4.43681651644086e-01 --1.54857313994574e+02 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0.00000000000000e+00 3.52340583612421e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_13_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_13_Coords.txt deleted file mode 100644 index 375fb47a..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_13_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.318647 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.88677309086297e-03 - 9.99429683992583e-01 -3.84398010521048e-03 - 9.98063017832965e-01 -3.96214815507257e-03 - 9.95573914266674e-01 -4.00057137726261e-03 - 9.92086309749559e-01 -3.97457367928264e-03 - 9.87686148675057e-01 -3.89551633167787e-03 - 9.82330525170640e-01 -3.77843615462504e-03 - 9.76011908335692e-01 -3.64599656672618e-03 - 9.68787467298381e-01 -3.52297262009936e-03 - 9.60674860259240e-01 -3.43214082565491e-03 - 9.51675358763677e-01 -3.25916814039515e-03 - 9.41827652746244e-01 -3.13485091846520e-03 - 9.31175295355131e-01 -3.09702334016245e-03 - 9.19730397431178e-01 -3.47735277272707e-03 - 9.07524559194720e-01 -3.61798234858645e-03 - 8.94610408070308e-01 -4.21681758471706e-03 - 8.81009696499435e-01 -5.30905213337190e-03 - 8.66747905197194e-01 -6.95638669717341e-03 - 8.51890258171205e-01 -9.18728387307661e-03 - 8.36469462621421e-01 -1.20421745685133e-02 - 8.20513485943698e-01 -1.55042032439111e-02 - 8.04073832217581e-01 -1.95718257205769e-02 - 7.87191529885653e-01 -2.42327825674124e-02 - 7.69897919101553e-01 -2.94953925097795e-02 - 7.52252341235159e-01 -3.53453830437986e-02 - 7.34291349178558e-01 -4.17561782481666e-02 - 7.16044924955764e-01 -4.86614945481548e-02 - 6.97571640033109e-01 -5.59741042284629e-02 - 6.78906186433687e-01 -6.36340857317376e-02 - 6.60080312620540e-01 -7.15153434679887e-02 - 6.41147517137212e-01 -7.95241000980543e-02 - 6.22137650968852e-01 -8.75608315252292e-02 - 6.03087998194415e-01 -9.55362950165535e-02 - 5.84045042118975e-01 -1.03366536893689e-01 - 5.65030897687003e-01 -1.10972755461888e-01 - 5.46088602779599e-01 -1.18297122331439e-01 - 5.27248673916899e-01 -1.25272300304559e-01 - 5.08535950506088e-01 -1.31866924008673e-01 - 4.89992355470388e-01 -1.38044536749180e-01 - 4.71632114506831e-01 -1.43781767342008e-01 - 4.53492503744347e-01 -1.49042217084384e-01 - 4.35593302897673e-01 -1.53801358774338e-01 - 4.17956065616942e-01 -1.58021064847024e-01 - 4.00609748442576e-01 -1.61703997004828e-01 - 3.83560931606009e-01 -1.64874218075122e-01 - 3.66843215733716e-01 -1.67539633268643e-01 - 3.50457316320503e-01 -1.69723801257368e-01 - 3.34434484008630e-01 -1.71438231935988e-01 - 3.18774100329315e-01 -1.72703644452672e-01 - 3.03499623121295e-01 -1.73535302265875e-01 - 2.88611293565648e-01 -1.73961522022757e-01 - 2.74124386665666e-01 -1.73967569563626e-01 - 2.60041455523719e-01 -1.73615351283184e-01 - 2.46374872015917e-01 -1.72891785258589e-01 - 2.33123443938834e-01 -1.71834746933106e-01 - 2.20293777810423e-01 -1.70457470386968e-01 - 2.07883282965331e-01 -1.68782174321022e-01 - 1.95902956391646e-01 -1.66840573353146e-01 - 1.84341253066628e-01 -1.64642118530581e-01 - 1.73213930954160e-01 -1.62216084804580e-01 - 1.62499176129638e-01 -1.59581529746380e-01 - 1.52214602777260e-01 -1.56738988841452e-01 - 1.42331759398971e-01 -1.53702991236013e-01 - 1.32872111539190e-01 -1.50499192644354e-01 - 1.23806439629760e-01 -1.47131415959986e-01 - 1.15147623386077e-01 -1.43628209321667e-01 - 1.06887208802748e-01 -1.40001227350336e-01 - 9.90071115215634e-02 -1.36255457110590e-01 - 9.15234043853439e-02 -1.32406169498632e-01 - 8.43970428172224e-02 -1.28444939561076e-01 - 7.76464790199521e-02 -1.24392259672683e-01 - 7.12479082120209e-02 -1.20250493629764e-01 - 6.51878662973747e-02 -1.16023524387341e-01 - 5.94874721274202e-02 -1.11739532353295e-01 - 5.41002464180900e-02 -1.07390004604875e-01 - 4.90378786701877e-02 -1.03003759163580e-01 - 4.43003497573338e-02 -9.85948791588736e-02 - 3.98423597346806e-02 -9.41542944018389e-02 - 3.56899752436130e-02 -8.97127983084216e-02 - 3.18292350050658e-02 -8.52608332488516e-02 - 2.82200072057899e-02 -8.07699813154801e-02 - 2.48925247792699e-02 -7.62798280611100e-02 - 2.18286683030034e-02 -7.17878704369970e-02 - 1.89846947131331e-02 -6.72355223228423e-02 - 1.63921917020335e-02 -6.27288062277139e-02 - 1.40446346341990e-02 -5.83308561780574e-02 - 1.18798249846349e-02 -5.39169408388137e-02 - 9.93094518736223e-03 -4.96061029258891e-02 - 8.21940795734749e-03 -4.54548861743847e-02 - 6.65838622137879e-03 -4.11341461169025e-02 - 5.26774192850643e-03 -3.67200985727644e-02 - 4.09515753852961e-03 -3.22769506746120e-02 - 3.09878859713640e-03 -2.74682258209055e-02 - 2.19660773551101e-03 -2.20932419495079e-02 - 1.46264176301869e-03 -1.72624322094160e-02 - 9.64484608297914e-04 -1.35027434739074e-02 - 5.99373867982851e-04 -9.89735672644611e-03 - 2.90086645599082e-04 -5.10662145847930e-03 - 7.80707788302466e-05 -1.14699069480167e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.22436624686423e-03 - 2.89878724192004e-04 4.58020875821276e-03 - 5.98775316682048e-04 8.81410041940714e-03 - 9.63326351634835e-04 1.24671686200768e-02 - 1.45966821282819e-03 1.62122554117209e-02 - 2.19097636449990e-03 2.10032350126191e-02 - 3.08997841959778e-03 2.70388719848978e-02 - 4.08271112470316e-03 3.27406711419058e-02 - 5.24853124383664e-03 3.78069311820844e-02 - 6.63128223001261e-03 4.26899071649104e-02 - 8.18368429859057e-03 4.72256526081546e-02 - 9.88361416849065e-03 5.15188776610099e-02 - 1.18176401547236e-02 5.60367587744284e-02 - 1.39661993216829e-02 6.06294060812255e-02 - 1.62951420791042e-02 6.52420812538140e-02 - 1.88631937781153e-02 6.99634504690100e-02 - 2.16807137532775e-02 7.47282287152275e-02 - 2.47159162958630e-02 7.94499439781466e-02 - 2.80064400105862e-02 8.41962179230978e-02 - 3.15762558914965e-02 8.89709469220644e-02 - 3.53948396168776e-02 9.37081744469339e-02 - 3.94949825480075e-02 9.84335204543342e-02 - 4.38979282781582e-02 1.03160552030096e-01 - 4.85758075737765e-02 1.07831737236157e-01 - 5.35679916138119e-02 1.12459514352561e-01 - 5.88818211488708e-02 1.17041307468516e-01 - 6.45001629027312e-02 1.21534734895495e-01 - 7.04692046391145e-02 1.25947495831980e-01 - 7.67740309924711e-02 1.30259390936231e-01 - 8.34162127168367e-02 1.34458770172386e-01 - 9.04290195190654e-02 1.38556280217472e-01 - 9.77906533229447e-02 1.42502841804153e-01 - 1.05536187198748e-01 1.46302854719866e-01 - 1.13658760041779e-01 1.49950377210598e-01 - 1.22161483318940e-01 1.53423774159371e-01 - 1.31067498602735e-01 1.56721718640139e-01 - 1.40354649921884e-01 1.59820822730127e-01 - 1.50055110786138e-01 1.62705477012277e-01 - 1.60148962661562e-01 1.65352487935489e-01 - 1.70658187899640e-01 1.67745752874824e-01 - 1.81574957422924e-01 1.69882001484326e-01 - 1.92907571409635e-01 1.71745340429433e-01 - 2.04657634577812e-01 1.73315534709870e-01 - 2.16817353069425e-01 1.74593444058291e-01 - 2.29396483963478e-01 1.75574842570378e-01 - 2.42377800694080e-01 1.76258031949681e-01 - 2.55773624268338e-01 1.76636580628478e-01 - 2.69566785632899e-01 1.76699331797916e-01 - 2.83765797226135e-01 1.76463042030302e-01 - 2.98347982887804e-01 1.75908712557000e-01 - 3.13318978785268e-01 1.75045069758733e-01 - 3.28658461892810e-01 1.73869178402439e-01 - 3.44364941645546e-01 1.72373888935953e-01 - 3.60419773725681e-01 1.70579150408941e-01 - 3.76811233766957e-01 1.68480089554922e-01 - 3.93525251020729e-01 1.66083220523290e-01 - 4.10538642553571e-01 1.63394461889728e-01 - 4.27843232490823e-01 1.60429303485594e-01 - 4.45406663468198e-01 1.57200083407677e-01 - 4.63222254103030e-01 1.53723137338579e-01 - 4.81251545655716e-01 1.50006018968342e-01 - 4.99481026671737e-01 1.46073750049586e-01 - 5.17879583085697e-01 1.41953047881452e-01 - 5.36417631367010e-01 1.37657474222537e-01 - 5.55075704909560e-01 1.33211583272055e-01 - 5.73808427242608e-01 1.28630448589503e-01 - 5.92596731105059e-01 1.23932232680115e-01 - 6.11401377553511e-01 1.19142815039112e-01 - 6.30186430605241e-01 1.14270436727691e-01 - 6.48926781663159e-01 1.09342879404743e-01 - 6.67570206424973e-01 1.04384221643560e-01 - 6.86088429590952e-01 9.94050962100429e-02 - 7.04445389043917e-01 9.44209702019478e-02 - 7.22592093722966e-01 8.94581154884182e-02 - 7.40501800453524e-01 8.45168934742565e-02 - 7.58125457122835e-01 7.96390649739472e-02 - 7.75421014376153e-01 7.48297913834028e-02 - 7.92362373587600e-01 7.01069129458996e-02 - 8.08894546151696e-01 6.54933472266714e-02 - 8.24974633014891e-01 6.09960890691258e-02 - 8.40576952273409e-01 5.66334298022270e-02 - 8.55652758808818e-01 5.24299053088858e-02 - 8.70162898882712e-01 4.83944448134549e-02 - 8.84085033071272e-01 4.45325598307973e-02 - 8.97361214262371e-01 4.08566858009572e-02 - 9.09954680076662e-01 3.73886903094429e-02 - 9.21851471402547e-01 3.41386847142628e-02 - 9.33012836658427e-01 3.11132821883773e-02 - 9.43389278969050e-01 2.83023395702333e-02 - 9.52973153850560e-01 2.56843368103016e-02 - 9.61743130827061e-01 2.32820875488657e-02 - 9.69640690675464e-01 2.11094691049735e-02 - 9.76664215898664e-01 1.91673082909301e-02 - 9.82815077112014e-01 1.74621896640299e-02 - 9.88028440045103e-01 1.60188405729297e-02 - 9.92304836603751e-01 1.48548331421504e-02 - 9.95693518775914e-01 1.38962467244040e-02 - 9.98120489340015e-01 1.31927957246045e-02 - 9.99443037908705e-01 1.29039810196147e-02 - 1.00000000000000e+00 1.26462639338406e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_14.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_14.dat index 18076cbb..fa19e710 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_14.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_14.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_14_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF14_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF14_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.933765 alpha0 ! 0-lift angle of attack, depends on airfoil. - 12.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -12.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-10.404161 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.702851 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.788718 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.971745 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.297918 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.013434 Cd0 ! 2D drag coefficient value at 0-lift. - -0.083711 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.014811 Cd0 ! 2D drag coefficient value at 0-lift. +-0.082690 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 3.32975743395306e-03 3.40626563480718e-02 4.87530856627876e-03 --1.77714285740401e+02 7.10036200652955e-02 3.66154518246064e-02 9.14545642204807e-02 --1.75428571400002e+02 1.43673157460731e-01 3.71700665925463e-02 1.82728922947064e-01 --1.73142857116900e+02 2.13980458384695e-01 3.73144559860746e-02 2.74597344796168e-01 --1.70857160423602e+02 2.82817491643002e-01 3.99544468208625e-02 3.65216863883154e-01 --1.68571631778825e+02 3.51069020568778e-01 4.79503407898186e-02 4.03525006655477e-01 --1.66285714267592e+02 4.19641256484413e-01 6.29063571078726e-02 4.08296089957386e-01 --1.63999999984490e+02 4.89406382184697e-01 8.53855017027857e-02 4.12437093193866e-01 --1.61714472886699e+02 5.61254511359863e-01 1.13806400865100e-01 4.18563382516625e-01 --1.59428371284127e+02 6.35621376098621e-01 1.46199992993186e-01 4.25949649215817e-01 --1.57142842639350e+02 7.10975097041862e-01 1.81919597148014e-01 4.43519830401275e-01 --1.54857313994574e+02 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0.00000000000000e+00 3.39827187802334e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_14_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_14_Coords.txt deleted file mode 100644 index d08b390d..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_14_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.314429 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -8.27871553328963e-03 - 9.99429683992583e-01 -8.17694617104345e-03 - 9.98063017832965e-01 -8.04451684214410e-03 - 9.95573914266674e-01 -7.72244162383767e-03 - 9.92086309749559e-01 -7.24716025614609e-03 - 9.87686148675057e-01 -6.64569410170722e-03 - 9.82330525170640e-01 -5.95380272447914e-03 - 9.76011908335692e-01 -5.22538439650025e-03 - 9.68787467298381e-01 -4.51935785986658e-03 - 9.60674860259240e-01 -3.88989021270606e-03 - 9.51675358763677e-01 -3.37927637976133e-03 - 9.41827652746244e-01 -2.93867677401337e-03 - 9.31175295355131e-01 -2.64132842214959e-03 - 9.19730397431178e-01 -2.69091714668401e-03 - 9.07524559194720e-01 -2.78990906469520e-03 - 8.94610408070308e-01 -3.32923275819804e-03 - 8.81009696499435e-01 -4.34981065019186e-03 - 8.66747905197194e-01 -5.90910733942243e-03 - 8.51890258171205e-01 -8.04036098325973e-03 - 8.36469462621421e-01 -1.07818477671093e-02 - 8.20513485943698e-01 -1.41115053085298e-02 - 8.04073832217581e-01 -1.80455457055439e-02 - 7.87191529885653e-01 -2.25680857672592e-02 - 7.69897919101553e-01 -2.77026852076914e-02 - 7.52252341235159e-01 -3.34265687444662e-02 - 7.34291349178558e-01 -3.97088681070492e-02 - 7.16044924955764e-01 -4.64834897380939e-02 - 6.97571640033109e-01 -5.36716424760686e-02 - 6.78906186433687e-01 -6.12195899160391e-02 - 6.60080312620540e-01 -6.89974897391596e-02 - 6.41147517137212e-01 -7.69159294736951e-02 - 6.22137650968852e-01 -8.48748642813526e-02 - 6.03087998194415e-01 -9.27855093408258e-02 - 5.84045042118975e-01 -1.00575786257714e-01 - 5.65030897687003e-01 -1.08144202870563e-01 - 5.46088602779599e-01 -1.15436104049726e-01 - 5.27248673916899e-01 -1.22381208045215e-01 - 5.08535950506088e-01 -1.28944317282347e-01 - 4.89992355470388e-01 -1.35090125646681e-01 - 4.71632114506831e-01 -1.40794175971114e-01 - 4.53492503744347e-01 -1.46019232223101e-01 - 4.35593302897673e-01 -1.50741760014200e-01 - 4.17956065616942e-01 -1.54932321173377e-01 - 4.00609748442576e-01 -1.58592958817935e-01 - 3.83560931606009e-01 -1.61746947866519e-01 - 3.66843215733716e-01 -1.64395962146827e-01 - 3.50457316320503e-01 -1.66565858829663e-01 - 3.34434484008630e-01 -1.68271159651299e-01 - 3.18774100329315e-01 -1.69528934073135e-01 - 3.03499623121295e-01 -1.70352077314962e-01 - 2.88611293565648e-01 -1.70773657430489e-01 - 2.74124386665666e-01 -1.70779379357585e-01 - 2.60041455523719e-01 -1.70423815640691e-01 - 2.46374872015917e-01 -1.69699164197061e-01 - 2.33123443938834e-01 -1.68644967643713e-01 - 2.20293777810423e-01 -1.67271850717293e-01 - 2.07883282965331e-01 -1.65599175674002e-01 - 1.95902956391646e-01 -1.63661226325076e-01 - 1.84341253066628e-01 -1.61464644333523e-01 - 1.73213930954160e-01 -1.59041762159976e-01 - 1.62499176129638e-01 -1.56406023126714e-01 - 1.52214602777260e-01 -1.53560032006020e-01 - 1.42331759398971e-01 -1.50522835245708e-01 - 1.32872111539190e-01 -1.47314626548021e-01 - 1.23806439629760e-01 -1.43944312437223e-01 - 1.15147623386077e-01 -1.40440974574981e-01 - 1.06887208802748e-01 -1.36809102262170e-01 - 9.90071115215634e-02 -1.33060031646956e-01 - 9.15234043853439e-02 -1.29206709560326e-01 - 8.43970428172224e-02 -1.25242729485241e-01 - 7.76464790199521e-02 -1.21189920904211e-01 - 7.12479082120209e-02 -1.17052037481686e-01 - 6.51878662973747e-02 -1.12833175116032e-01 - 5.94874721274202e-02 -1.08563727310970e-01 - 5.41002464180900e-02 -1.04239243840071e-01 - 4.90378786701877e-02 -9.98866008902117e-02 - 4.43003497573338e-02 -9.55174215988201e-02 - 3.98423597346806e-02 -9.11147322321570e-02 - 3.56899752436130e-02 -8.67148680312086e-02 - 3.18292350050658e-02 -8.23121254259856e-02 - 2.82200072057899e-02 -7.78741003236477e-02 - 2.48925247792699e-02 -7.34457960803803e-02 - 2.18286683030034e-02 -6.90290277462557e-02 - 1.89846947131331e-02 -6.45841412140313e-02 - 1.63921917020335e-02 -6.01992312256988e-02 - 1.40446346341990e-02 -5.59259806003653e-02 - 1.18798249846349e-02 -5.16373309249768e-02 - 9.93094518736223e-03 -4.74412135664175e-02 - 8.21940795734749e-03 -4.33634771030284e-02 - 6.65838622137879e-03 -3.91431927090829e-02 - 5.26774192850643e-03 -3.48319592588206e-02 - 4.09515753852961e-03 -3.05631387063286e-02 - 3.09878859713640e-03 -2.60671624812553e-02 - 2.19660773551101e-03 -2.10392469283146e-02 - 1.46264176301869e-03 -1.64862118686889e-02 - 9.64484608297914e-04 -1.31356720125604e-02 - 5.99373867982851e-04 -9.91916905069290e-03 - 2.90086645599082e-04 -5.42139359539821e-03 - 7.80707788302466e-05 -1.27008097327957e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.30639300498795e-03 - 2.89878724192004e-04 4.92461168114483e-03 - 5.98775316682048e-04 9.08209725739973e-03 - 9.63326351634835e-04 1.23875823659187e-02 - 1.45966821282819e-03 1.58036338406823e-02 - 2.19097636449990e-03 2.03842087783778e-02 - 3.08997841959778e-03 2.58833581240434e-02 - 4.08271112470316e-03 3.10653757019917e-02 - 5.24853124383664e-03 3.59037582265934e-02 - 6.63128223001261e-03 4.06215456122183e-02 - 8.18368429859057e-03 4.50569621135025e-02 - 9.88361416849065e-03 4.92699024567115e-02 - 1.18176401547236e-02 5.36370244055329e-02 - 1.39661993216829e-02 5.80817132923313e-02 - 1.62951420791042e-02 6.25349878013391e-02 - 1.88631937781153e-02 6.70944053578450e-02 - 2.16807137532775e-02 7.17134813252193e-02 - 2.47159162958630e-02 7.63093939737098e-02 - 2.80064400105862e-02 8.09380984640055e-02 - 3.15762558914965e-02 8.56003311673726e-02 - 3.53948396168776e-02 9.02303239682536e-02 - 3.94949825480075e-02 9.48535975862002e-02 - 4.38979282781582e-02 9.94842933840258e-02 - 4.85758075737765e-02 1.04067952478587e-01 - 5.35679916138119e-02 1.08612450634172e-01 - 5.88818211488708e-02 1.13122944202532e-01 - 6.45001629027312e-02 1.17550958423797e-01 - 7.04692046391145e-02 1.21908494903267e-01 - 7.67740309924711e-02 1.26172285704688e-01 - 8.34162127168367e-02 1.30326512580564e-01 - 9.04290195190654e-02 1.34378405451015e-01 - 9.77906533229447e-02 1.38290199742416e-01 - 1.05536187198748e-01 1.42063275265216e-01 - 1.13658760041779e-01 1.45686012133438e-01 - 1.22161483318940e-01 1.49131972461852e-01 - 1.31067498602735e-01 1.52404807965191e-01 - 1.40354649921884e-01 1.55483814162795e-01 - 1.50055110786138e-01 1.58354458683198e-01 - 1.60148962661562e-01 1.60994663046948e-01 - 1.70658187899640e-01 1.63379104239879e-01 - 1.81574957422924e-01 1.65511682813888e-01 - 1.92907571409635e-01 1.67377153223557e-01 - 2.04657634577812e-01 1.68947395070793e-01 - 2.16817353069425e-01 1.70234779049031e-01 - 2.29396483963478e-01 1.71222889687714e-01 - 2.42377800694080e-01 1.71921842445137e-01 - 2.55773624268338e-01 1.72315690374370e-01 - 2.69566785632899e-01 1.72400870878862e-01 - 2.83765797226135e-01 1.72189202021823e-01 - 2.98347982887804e-01 1.71660429919170e-01 - 3.13318978785268e-01 1.70827699816148e-01 - 3.28658461892810e-01 1.69693322705585e-01 - 3.44364941645546e-01 1.68244932477343e-01 - 3.60419773725681e-01 1.66503105870144e-01 - 3.76811233766957e-01 1.64459887220888e-01 - 3.93525251020729e-01 1.62124630236022e-01 - 4.10538642553571e-01 1.59509063912699e-01 - 4.27843232490823e-01 1.56617168080059e-01 - 4.45406663468198e-01 1.53469161495133e-01 - 4.63222254103030e-01 1.50077210700898e-01 - 4.81251545655716e-01 1.46449037173423e-01 - 4.99481026671737e-01 1.42610061474851e-01 - 5.17879583085697e-01 1.38591288470282e-01 - 5.36417631367010e-01 1.34402250297905e-01 - 5.55075704909560e-01 1.30063970526750e-01 - 5.73808427242608e-01 1.25596832012340e-01 - 5.92596731105059e-01 1.21011441948428e-01 - 6.11401377553511e-01 1.16334598624565e-01 - 6.30186430605241e-01 1.11575135318999e-01 - 6.48926781663159e-01 1.06759620202180e-01 - 6.67570206424973e-01 1.01906582938153e-01 - 6.86088429590952e-01 9.70328644947772e-02 - 7.04445389043917e-01 9.21516344737115e-02 - 7.22592093722966e-01 8.72863616875016e-02 - 7.40501800453524e-01 8.24417774782908e-02 - 7.58125457122835e-01 7.76560006140879e-02 - 7.75421014376153e-01 7.29377436375544e-02 - 7.92362373587600e-01 6.83056651939458e-02 - 8.08894546151696e-01 6.37831385443284e-02 - 8.24974633014891e-01 5.93702601020428e-02 - 8.40576952273409e-01 5.50904904077357e-02 - 8.55652758808818e-01 5.09718498052628e-02 - 8.70162898882712e-01 4.70168587253665e-02 - 8.84085033071272e-01 4.32375770953504e-02 - 8.97361214262371e-01 3.96404177985030e-02 - 9.09954680076662e-01 3.62490936839067e-02 - 9.21851471402547e-01 3.30707247732939e-02 - 9.33012836658427e-01 3.01164524322662e-02 - 9.43389278969050e-01 2.73779998180087e-02 - 9.52973153850560e-01 2.48351160093717e-02 - 9.61743130827061e-01 2.25042012511816e-02 - 9.69640690675464e-01 2.03952513836557e-02 - 9.76664215898664e-01 1.85063425177693e-02 - 9.82815077112014e-01 1.68457629996091e-02 - 9.88028440045103e-01 1.54354884683071e-02 - 9.92304836603751e-01 1.42902173942725e-02 - 9.95693518775914e-01 1.33579970360222e-02 - 9.98120489340015e-01 1.26790619156171e-02 - 9.99443037908705e-01 1.23726227154978e-02 - 1.00000000000000e+00 1.21511404121689e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_15.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_15.dat index b5e377b8..93653d94 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_15.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_15.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_15_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF15_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF15_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.869698 alpha0 ! 0-lift angle of attack, depends on airfoil. - 12.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -12.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-10.680572 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.757413 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.813218 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.982561 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.271763 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.013033 Cd0 ! 2D drag coefficient value at 0-lift. - -0.084717 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.014510 Cd0 ! 2D drag coefficient value at 0-lift. +-0.083575 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 3.32523560098604e-03 3.29752532173766e-02 4.86230532089150e-03 --1.77714285740401e+02 7.07255066217287e-02 3.61937342868806e-02 9.14438563204645e-02 --1.75428571400002e+02 1.43084290140781e-01 3.63410479895445e-02 1.82782186331179e-01 --1.73142857116900e+02 2.12919126803305e-01 3.56224811541872e-02 2.74522614082463e-01 --1.70857160423602e+02 2.81188004849118e-01 3.79611720396617e-02 3.65237806947464e-01 --1.68571631778825e+02 3.48845264640152e-01 4.68743520591458e-02 4.03534487922408e-01 --1.66285714267592e+02 4.16866784062595e-01 6.28076735606916e-02 4.08216537543400e-01 --1.63999999984490e+02 4.86194563571890e-01 8.54466639916253e-02 4.12378386753612e-01 --1.61714472886699e+02 5.57788002150531e-01 1.13418266100215e-01 4.18518600876152e-01 --1.59428371284127e+02 6.32096438594455e-01 1.45404216891411e-01 4.25797538291667e-01 --1.57142842639350e+02 7.07375114685342e-01 1.80875270840659e-01 4.43326611598076e-01 --1.54857313994574e+02 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0.00000000000000e+00 3.29453076082466e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_15_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_15_Coords.txt deleted file mode 100644 index 0561ef06..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_15_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.311212 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -1.13524000945410e-02 - 9.99429683992583e-01 -1.12093563347838e-02 - 9.98063017832965e-01 -1.09015473636677e-02 - 9.95573914266674e-01 -1.03271786543981e-02 - 9.92086309749559e-01 -9.53746778374337e-03 - 9.87686148675057e-01 -8.57039577146897e-03 - 9.82330525170640e-01 -7.47622491658978e-03 - 9.76011908335692e-01 -6.33071308699254e-03 - 9.68787467298381e-01 -5.21667435904163e-03 - 9.60674860259240e-01 -4.21024441642009e-03 - 9.51675358763677e-01 -3.44565286262152e-03 - 9.41827652746244e-01 -2.79402980544347e-03 - 9.31175295355131e-01 -2.32828930192312e-03 - 9.19730397431178e-01 -2.16271790883291e-03 - 9.07524559194720e-01 -2.23680966754710e-03 - 8.94610408070308e-01 -2.73426848188728e-03 - 8.81009696499435e-01 -3.70391087212246e-03 - 8.66747905197194e-01 -5.19886774540395e-03 - 8.51890258171205e-01 -7.25478884885514e-03 - 8.36469462621421e-01 -9.90795218767811e-03 - 8.20513485943698e-01 -1.31355371496544e-02 - 8.04073832217581e-01 -1.69644481602506e-02 - 7.87191529885653e-01 -2.13783306417664e-02 - 7.69897919101553e-01 -2.64112188582950e-02 - 7.52252341235159e-01 -3.20343067383293e-02 - 7.34291349178558e-01 -3.82125249732342e-02 - 7.16044924955764e-01 -4.48811489725719e-02 - 6.97571640033109e-01 -5.19678995866663e-02 - 6.78906186433687e-01 -5.94223050364155e-02 - 6.60080312620540e-01 -6.71143485282183e-02 - 6.41147517137212e-01 -7.49563127265249e-02 - 6.22137650968852e-01 -8.28485791877693e-02 - 6.03087998194415e-01 -9.07024021872224e-02 - 5.84045042118975e-01 -9.84519315625373e-02 - 5.65030897687003e-01 -1.05982131571353e-01 - 5.46088602779599e-01 -1.13239647444697e-01 - 5.27248673916899e-01 -1.20151694802301e-01 - 5.08535950506088e-01 -1.26680540512465e-01 - 4.89992355470388e-01 -1.32791521467140e-01 - 4.71632114506831e-01 -1.38458609820228e-01 - 4.53492503744347e-01 -1.43644989180387e-01 - 4.35593302897673e-01 -1.48327822915431e-01 - 4.17956065616942e-01 -1.52484933940135e-01 - 4.00609748442576e-01 -1.56117836503412e-01 - 3.83560931606009e-01 -1.59248498153771e-01 - 3.66843215733716e-01 -1.61874943248431e-01 - 3.50457316320503e-01 -1.64023551969778e-01 - 3.34434484008630e-01 -1.65711820203634e-01 - 3.18774100329315e-01 -1.66953179950717e-01 - 3.03499623121295e-01 -1.67760257940373e-01 - 2.88611293565648e-01 -1.68168173912148e-01 - 2.74124386665666e-01 -1.68164819576549e-01 - 2.60041455523719e-01 -1.67796821624935e-01 - 2.46374872015917e-01 -1.67062780195501e-01 - 2.33123443938834e-01 -1.66001566811679e-01 - 2.20293777810423e-01 -1.64622955629457e-01 - 2.07883282965331e-01 -1.62943795177698e-01 - 1.95902956391646e-01 -1.60999764323607e-01 - 1.84341253066628e-01 -1.58796029358294e-01 - 1.73213930954160e-01 -1.56366272958405e-01 - 1.62499176129638e-01 -1.53720515502186e-01 - 1.52214602777260e-01 -1.50862647826324e-01 - 1.42331759398971e-01 -1.47815725938892e-01 - 1.32872111539190e-01 -1.44595659067693e-01 - 1.23806439629760e-01 -1.41214929286108e-01 - 1.15147623386077e-01 -1.37703042314240e-01 - 1.06887208802748e-01 -1.34059960439712e-01 - 9.90071115215634e-02 -1.30300714334689e-01 - 9.15234043853439e-02 -1.26438011436660e-01 - 8.43970428172224e-02 -1.22466492879759e-01 - 7.76464790199521e-02 -1.18409196843110e-01 - 7.12479082120209e-02 -1.14271610318515e-01 - 6.51878662973747e-02 -1.10057206174565e-01 - 5.94874721274202e-02 -1.05798772088795e-01 - 5.41002464180900e-02 -1.01494874808662e-01 - 4.90378786701877e-02 -9.71703752783246e-02 - 4.43003497573338e-02 -9.28357022546903e-02 - 3.98423597346806e-02 -8.84665352952360e-02 - 3.56899752436130e-02 -8.41047426945829e-02 - 3.18292350050658e-02 -7.97484770613801e-02 - 2.82200072057899e-02 -7.53604931443538e-02 - 2.48925247792699e-02 -7.09908795090496e-02 - 2.18286683030034e-02 -6.66448727525559e-02 - 1.89846947131331e-02 -6.22972259565916e-02 - 1.63921917020335e-02 -5.80206729856851e-02 - 1.40446346341990e-02 -5.38574489225618e-02 - 1.18798249846349e-02 -4.96810189887660e-02 - 9.93094518736223e-03 -4.55889642287948e-02 - 8.21940795734749e-03 -4.15854050778567e-02 - 6.65838622137879e-03 -3.74633453415347e-02 - 5.26774192850643e-03 -3.32578836153755e-02 - 4.09515753852961e-03 -2.91475949272598e-02 - 3.09878859713640e-03 -2.49297733487062e-02 - 2.19660773551101e-03 -2.02322609340171e-02 - 1.46264176301869e-03 -1.59404549617611e-02 - 9.64484608297914e-04 -1.28774965635051e-02 - 5.99373867982851e-04 -9.90576974667627e-03 - 2.90086645599082e-04 -5.62915802115287e-03 - 7.80707788302466e-05 -1.38419348317654e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.36379912616541e-03 - 2.89878724192004e-04 5.16564078408573e-03 - 5.98775316682048e-04 9.26965384635786e-03 - 9.63326351634835e-04 1.23318842223523e-02 - 1.45966821282819e-03 1.55005452838926e-02 - 2.19097636449990e-03 1.98831930121886e-02 - 3.08997841959778e-03 2.49104895701814e-02 - 4.08271112470316e-03 2.96439287935238e-02 - 5.24853124383664e-03 3.42785271428763e-02 - 6.63128223001261e-03 3.88442941332029e-02 - 8.18368429859057e-03 4.31874509656638e-02 - 9.88361416849065e-03 4.73266167977158e-02 - 1.18176401547236e-02 5.15635021516681e-02 - 1.39661993216829e-02 5.58802483985975e-02 - 1.62951420791042e-02 6.01969240960953e-02 - 1.88631937781153e-02 6.46170501502717e-02 - 2.16807137532775e-02 6.91095033891391e-02 - 2.47159162958630e-02 7.35963965608490e-02 - 2.80064400105862e-02 7.81221765352152e-02 - 3.15762558914965e-02 8.26852968108571e-02 - 3.53948396168776e-02 8.72214668657434e-02 - 3.94949825480075e-02 9.17558154567369e-02 - 4.38979282781582e-02 9.63032000090056e-02 - 4.85758075737765e-02 1.00810846927012e-01 - 5.35679916138119e-02 1.05283718131042e-01 - 5.88818211488708e-02 1.09732853627244e-01 - 6.45001629027312e-02 1.14105219738737e-01 - 7.04692046391145e-02 1.18416442716965e-01 - 7.67740309924711e-02 1.22640513458415e-01 - 8.34162127168367e-02 1.26758525665423e-01 - 9.04290195190654e-02 1.30774524815199e-01 - 9.77906533229447e-02 1.34659968732521e-01 - 1.05536187198748e-01 1.38414394740971e-01 - 1.13658760041779e-01 1.42020029240827e-01 - 1.22161483318940e-01 1.45448907966717e-01 - 1.31067498602735e-01 1.48706848977763e-01 - 1.40354649921884e-01 1.51775730507123e-01 - 1.50055110786138e-01 1.54641564042575e-01 - 1.60148962661562e-01 1.57283511918169e-01 - 1.70658187899640e-01 1.59669520310222e-01 - 1.81574957422924e-01 1.61808140614164e-01 - 1.92907571409635e-01 1.63684497699495e-01 - 2.04657634577812e-01 1.65265081225541e-01 - 2.16817353069425e-01 1.66570207571639e-01 - 2.29396483963478e-01 1.67574781512655e-01 - 2.42377800694080e-01 1.68297324856264e-01 - 2.55773624268338e-01 1.68715045895551e-01 - 2.69566785632899e-01 1.68829989387034e-01 - 2.83765797226135e-01 1.68649168898283e-01 - 2.98347982887804e-01 1.68153239846662e-01 - 3.13318978785268e-01 1.67356828685188e-01 - 3.28658461892810e-01 1.66266624750172e-01 - 3.44364941645546e-01 1.64866991258053e-01 - 3.60419773725681e-01 1.63178787154812e-01 - 3.76811233766957e-01 1.61190924755408e-01 - 3.93525251020729e-01 1.58916115602935e-01 - 4.10538642553571e-01 1.56368805339346e-01 - 4.27843232490823e-01 1.53545706885602e-01 - 4.45406663468198e-01 1.50471830261141e-01 - 4.63222254103030e-01 1.47156728327873e-01 - 4.81251545655716e-01 1.43607755660661e-01 - 4.99481026671737e-01 1.39850702404706e-01 - 5.17879583085697e-01 1.35918801576833e-01 - 5.36417631367010e-01 1.31819490186357e-01 - 5.55075704909560e-01 1.27571393479128e-01 - 5.73808427242608e-01 1.23198087884675e-01 - 5.92596731105059e-01 1.18704783686898e-01 - 6.11401377553511e-01 1.14119333493067e-01 - 6.30186430605241e-01 1.09450735536018e-01 - 6.48926781663159e-01 1.04724510885870e-01 - 6.67570206424973e-01 9.99556057903572e-02 - 6.86088429590952e-01 9.51646755475449e-02 - 7.04445389043917e-01 9.03640017724712e-02 - 7.22592093722966e-01 8.55746886935009e-02 - 7.40501800453524e-01 8.08050592279156e-02 - 7.58125457122835e-01 7.60903271996976e-02 - 7.75421014376153e-01 7.14420611852513e-02 - 7.92362373587600e-01 6.68794010367297e-02 - 8.08894546151696e-01 6.24261567953823e-02 - 8.24974633014891e-01 5.80776467246580e-02 - 8.40576952273409e-01 5.38612458021558e-02 - 8.55652758808818e-01 4.98066918709917e-02 - 8.70162898882712e-01 4.59128600095281e-02 - 8.84085033071272e-01 4.21962573245077e-02 - 8.97361214262371e-01 3.86593508757759e-02 - 9.09954680076662e-01 3.53265688298009e-02 - 9.21851471402547e-01 3.22031265756426e-02 - 9.33012836658427e-01 2.93036071293325e-02 - 9.43389278969050e-01 2.66215020508833e-02 - 9.52973153850560e-01 2.41375819799427e-02 - 9.61743130827061e-01 2.18634338337469e-02 - 9.69640690675464e-01 1.98059915433614e-02 - 9.76664215898664e-01 1.79607277602864e-02 - 9.82815077112014e-01 1.63367462299270e-02 - 9.88028440045103e-01 1.49526654891766e-02 - 9.92304836603751e-01 1.38183589479466e-02 - 9.95693518775914e-01 1.29105694403987e-02 - 9.98120489340015e-01 1.22564092235140e-02 - 9.99443037908705e-01 1.19320918592969e-02 - 1.00000000000000e+00 1.17481014299336e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_16.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_16.dat index 7d491714..e55f5cf9 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_16.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_16.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_16_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF16_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF16_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.819411 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-10.922246 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.779244 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.831506 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.981012 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.244139 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.012621 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085412 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.014175 Cd0 ! 2D drag coefficient value at 0-lift. +-0.084189 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 3.32338549028063e-03 3.17451547713950e-02 4.85698503514200e-03 --1.77714285740401e+02 7.03729053027276e-02 3.56013526344839e-02 9.14400983030462e-02 --1.75428571400002e+02 1.42334895994140e-01 3.53409930704200e-02 1.82803979077147e-01 --1.73142857116900e+02 2.11573290459220e-01 3.40423772209134e-02 2.74492037965553e-01 --1.70857160423602e+02 2.79131079056225e-01 3.63432957792343e-02 3.65245142009559e-01 --1.68571631778825e+02 3.46047361946326e-01 4.59267958272648e-02 4.03537803413340e-01 --1.66285714267592e+02 4.13381953790089e-01 6.26655720776269e-02 4.08118508859305e-01 --1.63999999984490e+02 4.82161016950025e-01 8.54716885792594e-02 4.12304890626039e-01 --1.61714472886699e+02 5.53428041445021e-01 1.13259460525375e-01 4.18462218081386e-01 --1.59428371284127e+02 6.27653369451479e-01 1.45078624615947e-01 4.25608459375190e-01 --1.57142842639350e+02 7.02855713061396e-01 1.80447984097591e-01 4.43087419592186e-01 --1.54857313994574e+02 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0.00000000000000e+00 3.18309470116001e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_16_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_16_Coords.txt deleted file mode 100644 index 483d1f59..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_16_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.308548 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -1.26100000000000e-02 - 9.99429683992583e-01 -1.24500687954274e-02 - 9.98063017832965e-01 -1.20705031371576e-02 - 9.95573914266674e-01 -1.13929083927954e-02 - 9.92086309749559e-01 -1.04745484999915e-02 - 9.87686148675057e-01 -9.35788862888294e-03 - 9.82330525170640e-01 -8.09912488134332e-03 - 9.76011908335692e-01 -6.78295899218010e-03 - 9.68787467298381e-01 -5.50198182828971e-03 - 9.60674860259240e-01 -4.34131753348065e-03 - 9.51675358763677e-01 -3.35747808138093e-03 - 9.41827652746244e-01 -2.57577895863054e-03 - 9.31175295355131e-01 -2.01901595562735e-03 - 9.19730397431178e-01 -1.74253894586038e-03 - 9.07524559194720e-01 -1.79195589019341e-03 - 8.94610408070308e-01 -2.24664836078377e-03 - 8.81009696499435e-01 -3.16703856979118e-03 - 8.66747905197194e-01 -4.60063725222115e-03 - 8.51890258171205e-01 -6.58285355199009e-03 - 8.36469462621421e-01 -9.14736448781045e-03 - 8.20513485943698e-01 -1.22767544080848e-02 - 8.04073832217581e-01 -1.60016864791085e-02 - 7.87191529885653e-01 -2.03088930956254e-02 - 7.69897919101553e-01 -2.52397230888492e-02 - 7.52252341235159e-01 -3.07617334917572e-02 - 7.34291349178558e-01 -3.68344470347920e-02 - 7.16044924955764e-01 -4.33968216234823e-02 - 6.97571640033109e-01 -5.03823589882870e-02 - 6.78906186433687e-01 -5.77407932212508e-02 - 6.60080312620540e-01 -6.53459389439703e-02 - 6.41147517137212e-01 -7.31093581435309e-02 - 6.22137650968852e-01 -8.09327297309639e-02 - 6.03087998194415e-01 -8.87266931878093e-02 - 5.84045042118975e-01 -9.64250311287520e-02 - 5.65030897687003e-01 -1.03908464657037e-01 - 5.46088602779599e-01 -1.11122616034924e-01 - 5.27248673916899e-01 -1.17992661452588e-01 - 5.08535950506088e-01 -1.24479253443181e-01 - 4.89992355470388e-01 -1.30547276390113e-01 - 4.71632114506831e-01 -1.36169325843035e-01 - 4.53492503744347e-01 -1.41309234878840e-01 - 4.35593302897673e-01 -1.45946039032765e-01 - 4.17956065616942e-01 -1.50063321090746e-01 - 4.00609748442576e-01 -1.53661824682661e-01 - 3.83560931606009e-01 -1.56761109849289e-01 - 3.66843215733716e-01 -1.59359016280751e-01 - 3.50457316320503e-01 -1.61480104275853e-01 - 3.34434484008630e-01 -1.63143976348947e-01 - 3.18774100329315e-01 -1.64361798025707e-01 - 3.03499623121295e-01 -1.65147323055363e-01 - 2.88611293565648e-01 -1.65534689725736e-01 - 2.74124386665666e-01 -1.65515830302489e-01 - 2.60041455523719e-01 -1.65129566581791e-01 - 2.46374872015917e-01 -1.64381227908490e-01 - 2.33123443938834e-01 -1.63307145604311e-01 - 2.20293777810423e-01 -1.61916842701056e-01 - 2.07883282965331e-01 -1.60226296460540e-01 - 1.95902956391646e-01 -1.58270780752437e-01 - 1.84341253066628e-01 -1.56055064257814e-01 - 1.73213930954160e-01 -1.53613424829182e-01 - 1.62499176129638e-01 -1.50953056759462e-01 - 1.52214602777260e-01 -1.48080239556514e-01 - 1.42331759398971e-01 -1.45020392705416e-01 - 1.32872111539190e-01 -1.41786844275258e-01 - 1.23806439629760e-01 -1.38394081450807e-01 - 1.15147623386077e-01 -1.34872281298632e-01 - 1.06887208802748e-01 -1.31218755307541e-01 - 9.90071115215634e-02 -1.27450932573353e-01 - 9.15234043853439e-02 -1.23582417352718e-01 - 8.43970428172224e-02 -1.19608841993309e-01 - 7.76464790199521e-02 -1.15554012940927e-01 - 7.12479082120209e-02 -1.11425055260973e-01 - 6.51878662973747e-02 -1.07225128694727e-01 - 5.94874721274202e-02 -1.02988148533869e-01 - 5.41002464180900e-02 -9.87145661358714e-02 - 4.90378786701877e-02 -9.44274983893074e-02 - 4.43003497573338e-02 -9.01365908394866e-02 - 3.98423597346806e-02 -8.58139963300236e-02 - 3.56899752436130e-02 -8.15046651333854e-02 - 3.18292350050658e-02 -7.72091477079204e-02 - 2.82200072057899e-02 -7.28891467100779e-02 - 2.48925247792699e-02 -6.85961541646526e-02 - 2.18286683030034e-02 -6.43378784877907e-02 - 1.89846947131331e-02 -6.00950837351830e-02 - 1.63921917020335e-02 -5.59321963709591e-02 - 1.40446346341990e-02 -5.18821200462443e-02 - 1.18798249846349e-02 -4.78218158914443e-02 - 9.93094518736223e-03 -4.38431920985404e-02 - 8.21940795734749e-03 -3.99381312632367e-02 - 6.65838622137879e-03 -3.59378277671966e-02 - 5.26774192850643e-03 -3.18715342691420e-02 - 4.09515753852961e-03 -2.79310083203613e-02 - 3.09878859713640e-03 -2.39683484747496e-02 - 2.19660773551101e-03 -1.96164907724018e-02 - 1.46264176301869e-03 -1.55901304546000e-02 - 9.64484608297914e-04 -1.26766647231428e-02 - 5.99373867982851e-04 -9.77606212535752e-03 - 2.90086645599082e-04 -5.66955948311493e-03 - 7.80707788302466e-05 -1.43570133737620e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.38728687551863e-03 - 2.89878724192004e-04 5.26425798797601e-03 - 5.98775316682048e-04 9.34639273866824e-03 - 9.63326351634835e-04 1.23090952930762e-02 - 1.45966821282819e-03 1.53223356903517e-02 - 2.19097636449990e-03 1.94824752845196e-02 - 3.08997841959778e-03 2.40739918594412e-02 - 4.08271112470316e-03 2.84315978452799e-02 - 5.24853124383664e-03 3.28578757472612e-02 - 6.63128223001261e-03 3.72600361633042e-02 - 8.18368429859057e-03 4.14943703162430e-02 - 9.88361416849065e-03 4.55453768517104e-02 - 1.18176401547236e-02 4.96572157035563e-02 - 1.39661993216829e-02 5.38517102987149e-02 - 1.62951420791042e-02 5.80393264120705e-02 - 1.88631937781153e-02 6.23281170772017e-02 - 2.16807137532775e-02 6.66977389948486e-02 - 2.47159162958630e-02 7.10735470351849e-02 - 2.80064400105862e-02 7.54928784357786e-02 - 3.15762558914965e-02 7.99530745265847e-02 - 3.53948396168776e-02 8.43918477745959e-02 - 3.94949825480075e-02 8.88334693742878e-02 - 4.38979282781582e-02 9.32928377220895e-02 - 4.85758075737765e-02 9.77191845704017e-02 - 5.35679916138119e-02 1.02116030781650e-01 - 5.88818211488708e-02 1.06496714439934e-01 - 6.45001629027312e-02 1.10806447665208e-01 - 7.04692046391145e-02 1.15063675703670e-01 - 7.67740309924711e-02 1.19240571264768e-01 - 8.34162127168367e-02 1.23316263116734e-01 - 9.04290195190654e-02 1.27292028802868e-01 - 9.77906533229447e-02 1.31146114407364e-01 - 1.05536187198748e-01 1.34876102549999e-01 - 1.13658760041779e-01 1.38460176671430e-01 - 1.22161483318940e-01 1.41869829223881e-01 - 1.31067498602735e-01 1.45111634945064e-01 - 1.40354649921884e-01 1.48169163536710e-01 - 1.50055110786138e-01 1.51028861011175e-01 - 1.60148962661562e-01 1.53670843431024e-01 - 1.70658187899640e-01 1.56059205816028e-01 - 1.81574957422924e-01 1.58204593546453e-01 - 1.92907571409635e-01 1.60092208278256e-01 - 2.04657634577812e-01 1.61686482100959e-01 - 2.16817353069425e-01 1.63011059045074e-01 - 2.29396483963478e-01 1.64036113874917e-01 - 2.42377800694080e-01 1.64784922690675e-01 - 2.55773624268338e-01 1.65231030235340e-01 - 2.69566785632899e-01 1.65379596889106e-01 - 2.83765797226135e-01 1.65233543295160e-01 - 2.98347982887804e-01 1.64776030196773e-01 - 3.13318978785268e-01 1.64020622212247e-01 - 3.28658461892810e-01 1.62977641576707e-01 - 3.44364941645546e-01 1.61630592153943e-01 - 3.60419773725681e-01 1.59998651272686e-01 - 3.76811233766957e-01 1.58069981479222e-01 - 3.93525251020729e-01 1.55859310082454e-01 - 4.10538642553571e-01 1.53381230451562e-01 - 4.27843232490823e-01 1.50629616697552e-01 - 4.45406663468198e-01 1.47631392912683e-01 - 4.63222254103030e-01 1.44394576986685e-01 - 4.81251545655716e-01 1.40925529311111e-01 - 4.99481026671737e-01 1.37250821967516e-01 - 5.17879583085697e-01 1.33403132938047e-01 - 5.36417631367010e-01 1.29390507269776e-01 - 5.55075704909560e-01 1.25229908428551e-01 - 5.73808427242608e-01 1.20945218446081e-01 - 5.92596731105059e-01 1.16539325808337e-01 - 6.11401377553511e-01 1.12040235132929e-01 - 6.30186430605241e-01 1.07457048498423e-01 - 6.48926781663159e-01 1.02814628537720e-01 - 6.67570206424973e-01 9.81252841756307e-02 - 6.86088429590952e-01 9.34115824935454e-02 - 7.04445389043917e-01 8.86867431126987e-02 - 7.22592093722966e-01 8.39687568390500e-02 - 7.40501800453524e-01 7.92695230873123e-02 - 7.58125457122835e-01 7.46219425137931e-02 - 7.75421014376153e-01 7.00396827649668e-02 - 7.92362373587600e-01 6.55425272002120e-02 - 8.08894546151696e-01 6.11541079949266e-02 - 8.24974633014891e-01 5.68669628007894e-02 - 8.40576952273409e-01 5.27114409763169e-02 - 8.55652758808818e-01 4.87175428895656e-02 - 8.70162898882712e-01 4.48827114895073e-02 - 8.84085033071272e-01 4.12261665490823e-02 - 8.97361214262371e-01 3.77477429382950e-02 - 9.09954680076662e-01 3.44723248222539e-02 - 9.21851471402547e-01 3.14035342291393e-02 - 9.33012836658427e-01 2.85587643030542e-02 - 9.43389278969050e-01 2.59330389902550e-02 - 9.52973153850560e-01 2.35089073876192e-02 - 9.61743130827061e-01 2.12937909078101e-02 - 9.69640690675464e-01 1.92921710835133e-02 - 9.76664215898664e-01 1.74970509052354e-02 - 9.82815077112014e-01 1.59180887407559e-02 - 9.88028440045103e-01 1.45710543205876e-02 - 9.92304836603751e-01 1.34634128858945e-02 - 9.95693518775914e-01 1.25858572124191e-02 - 9.98120489340015e-01 1.19570877123489e-02 - 9.99443037908705e-01 1.16143542514621e-02 - 1.00000000000000e+00 1.14700000000000e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_17.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_17.dat index 4929450f..ada39cff 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_17.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_17.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_17_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF17_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF17_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.773651 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-11.140103 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.774068 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.973451 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.968157 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.212597 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.012184 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085826 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.013760 Cd0 ! 2D drag coefficient value at 0-lift. +-0.084590 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 3.89305221781797e-03 3.02025875369639e-02 4.86327340373760e-03 --1.77714285740401e+02 6.97031191085059e-02 3.44827673688663e-02 9.14490658024776e-02 --1.75428571400002e+02 1.40911296440873e-01 3.39658207817165e-02 1.82777761348403e-01 --1.73142857116900e+02 2.09295595273037e-01 3.25058668275593e-02 2.74529933345755e-01 --1.70857160423602e+02 2.75894338115755e-01 3.50304788315164e-02 3.65223763640833e-01 --1.68571631778825e+02 3.41799081131833e-01 4.50827569059231e-02 4.03338504838116e-01 --1.66285714267592e+02 4.08170142026872e-01 6.24111417164305e-02 4.07568651790028e-01 --1.63999999984490e+02 4.76127574378796e-01 8.54441462993828e-02 4.11418792312521e-01 --1.61714472886699e+02 5.46796726456801e-01 1.13320382788880e-01 4.17297858850372e-01 --1.59428371284127e+02 6.20640527269063e-01 1.45195434582703e-01 4.24115056338463e-01 --1.57142842639350e+02 6.95417524180717e-01 1.80593465337604e-01 4.41474870877542e-01 --1.54857313994574e+02 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0.00000000000000e+00 3.05414951794391e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_17_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_17_Coords.txt deleted file mode 100644 index a57097b1..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_17_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.306179 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -1.22924115268844e-02 - 9.99429683992583e-01 -1.21354188977382e-02 - 9.98063017832965e-01 -1.17629321141405e-02 - 9.95573914266674e-01 -1.10983130661520e-02 - 9.92086309749559e-01 -1.01981398582719e-02 - 9.87686148675057e-01 -9.10532053528230e-03 - 9.82330525170640e-01 -7.87265260283329e-03 - 9.76011908335692e-01 -6.58013613054340e-03 - 9.68787467298381e-01 -5.31680759363365e-03 - 9.60674860259240e-01 -4.16496804363483e-03 - 9.51675358763677e-01 -3.05175750330147e-03 - 9.41827652746244e-01 -2.21106856183785e-03 - 9.31175295355131e-01 -1.62172781533416e-03 - 9.19730397431178e-01 -1.30993643273559e-03 - 9.07524559194720e-01 -1.33525574214787e-03 - 8.94610408070308e-01 -1.74778667208556e-03 - 8.81009696499435e-01 -2.62180201199088e-03 - 8.66747905197194e-01 -3.99821951073766e-03 - 8.51890258171205e-01 -5.91020638512151e-03 - 8.36469462621421e-01 -8.38780279378663e-03 - 8.20513485943698e-01 -1.14237411687929e-02 - 8.04073832217581e-01 -1.50468490226365e-02 - 7.87191529885653e-01 -1.92495065240722e-02 - 7.69897919101553e-01 -2.40782850730006e-02 - 7.52252341235159e-01 -2.94988489324419e-02 - 7.34291349178558e-01 -3.54637161971435e-02 - 7.16044924955764e-01 -4.19179445185118e-02 - 6.97571640033109e-01 -4.88008214620099e-02 - 6.78906186433687e-01 -5.60592272065436e-02 - 6.60080312620540e-01 -6.35749450765822e-02 - 6.41147517137212e-01 -7.12563165049790e-02 - 6.22137650968852e-01 -7.90074885072114e-02 - 6.03087998194415e-01 -8.67379566985340e-02 - 5.84045042118975e-01 -9.43738706391404e-02 - 5.65030897687003e-01 -1.01801274106387e-01 - 5.46088602779599e-01 -1.08962238221174e-01 - 5.27248673916899e-01 -1.15780027137057e-01 - 5.08535950506088e-01 -1.22214611087625e-01 - 4.89992355470388e-01 -1.28229476320046e-01 - 4.71632114506831e-01 -1.33795718314774e-01 - 4.53492503744347e-01 -1.38878025714880e-01 - 4.35593302897673e-01 -1.43459043675503e-01 - 4.17956065616942e-01 -1.47527191650019e-01 - 4.00609748442576e-01 -1.51081753496205e-01 - 3.83560931606009e-01 -1.54138462775403e-01 - 3.66843215733716e-01 -1.56699222284159e-01 - 3.50457316320503e-01 -1.58783511450739e-01 - 3.34434484008630e-01 -1.60412306251821e-01 - 3.18774100329315e-01 -1.61595586246410e-01 - 3.03499623121295e-01 -1.62350828101969e-01 - 2.88611293565648e-01 -1.62706490949582e-01 - 2.74124386665666e-01 -1.62662040776121e-01 - 2.60041455523719e-01 -1.62246936818190e-01 - 2.46374872015917e-01 -1.61475416178325e-01 - 2.33123443938834e-01 -1.60377694858760e-01 - 2.20293777810423e-01 -1.58964337529987e-01 - 2.07883282965331e-01 -1.57252242516453e-01 - 1.95902956391646e-01 -1.55273796589555e-01 - 1.84341253066628e-01 -1.53035013910412e-01 - 1.73213930954160e-01 -1.50569434664346e-01 - 1.62499176129638e-01 -1.47882025694145e-01 - 1.52214602777260e-01 -1.44983125058055e-01 - 1.42331759398971e-01 -1.41898922879192e-01 - 1.32872111539190e-01 -1.38642280623009e-01 - 1.23806439629760e-01 -1.35227276987614e-01 - 1.15147623386077e-01 -1.31685631277134e-01 - 1.06887208802748e-01 -1.28014577267598e-01 - 9.90071115215634e-02 -1.24231854803350e-01 - 9.15234043853439e-02 -1.20354474148793e-01 - 8.43970428172224e-02 -1.16379313584583e-01 - 7.76464790199521e-02 -1.12330078366755e-01 - 7.12479082120209e-02 -1.08216512723416e-01 - 6.51878662973747e-02 -1.04041101010427e-01 - 5.94874721274202e-02 -9.98377101237248e-02 - 5.41002464180900e-02 -9.56072336782816e-02 - 4.90378786701877e-02 -9.13704283218292e-02 - 4.43003497573338e-02 -8.71362043674260e-02 - 3.98423597346806e-02 -8.28785677332970e-02 - 3.56899752436130e-02 -7.86431236243857e-02 - 3.18292350050658e-02 -7.44313024978041e-02 - 2.82200072057899e-02 -7.02083026198505e-02 - 2.48925247792699e-02 -6.60218619853511e-02 - 2.18286683030034e-02 -6.18816080650314e-02 - 1.89846947131331e-02 -5.77633352835677e-02 - 1.63921917020335e-02 -5.37315767868472e-02 - 1.40446346341990e-02 -4.98078419653765e-02 - 1.18798249846349e-02 -4.58786229023104e-02 - 9.93094518736223e-03 -4.20350013607287e-02 - 8.21940795734749e-03 -3.82647169936051e-02 - 6.65838622137879e-03 -3.44223153422255e-02 - 5.26774192850643e-03 -3.05404247774558e-02 - 4.09515753852961e-03 -2.67904971729354e-02 - 3.09878859713640e-03 -2.30737446190104e-02 - 2.19660773551101e-03 -1.90800391995441e-02 - 1.46264176301869e-03 -1.52964366837520e-02 - 9.64484608297914e-04 -1.24285975841936e-02 - 5.99373867982851e-04 -9.46304922859470e-03 - 2.90086645599082e-04 -5.43128565446029e-03 - 7.80707788302466e-05 -1.38770189708845e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.34239594172728e-03 - 2.89878724192004e-04 5.09981100637204e-03 - 5.98775316682048e-04 9.21439577504249e-03 - 9.63326351634835e-04 1.22525120177365e-02 - 1.45966821282819e-03 1.52074423701068e-02 - 2.19097636449990e-03 1.91283029070339e-02 - 3.08997841959778e-03 2.32975957804413e-02 - 4.08271112470316e-03 2.73304428404777e-02 - 5.24853124383664e-03 3.14999323073432e-02 - 6.63128223001261e-03 3.56854856010754e-02 - 8.18368429859057e-03 3.97685798832071e-02 - 9.88361416849065e-03 4.36958323882819e-02 - 1.18176401547236e-02 4.76760138913191e-02 - 1.39661993216829e-02 5.17436402183481e-02 - 1.62951420791042e-02 5.57989672994936e-02 - 1.88631937781153e-02 5.99532313131868e-02 - 2.16807137532775e-02 6.41908872283867e-02 - 2.47159162958630e-02 6.84395996571639e-02 - 2.80064400105862e-02 7.27349737972973e-02 - 3.15762558914965e-02 7.70719492533971e-02 - 3.53948396168776e-02 8.13923487958843e-02 - 3.94949825480075e-02 8.57210930290682e-02 - 4.38979282781582e-02 9.00728098952025e-02 - 4.85758075737765e-02 9.43993165745321e-02 - 5.35679916138119e-02 9.87048146102697e-02 - 5.88818211488708e-02 1.02998721071815e-01 - 6.45001629027312e-02 1.07229231892117e-01 - 7.04692046391145e-02 1.11416876251154e-01 - 7.67740309924711e-02 1.15533206892608e-01 - 8.34162127168367e-02 1.19556792939349e-01 - 9.04290195190654e-02 1.23486322250131e-01 - 9.77906533229447e-02 1.27303305441236e-01 - 1.05536187198748e-01 1.31003722675437e-01 - 1.13658760041779e-01 1.34562907607234e-01 - 1.22161483318940e-01 1.37955564544099e-01 - 1.31067498602735e-01 1.41185000217597e-01 - 1.40354649921884e-01 1.44235725885463e-01 - 1.50055110786138e-01 1.47093744586101e-01 - 1.60148962661562e-01 1.49740814375320e-01 - 1.70658187899640e-01 1.52141362754514e-01 - 1.81574957422924e-01 1.54303139811103e-01 - 1.92907571409635e-01 1.56210822021221e-01 - 2.04657634577812e-01 1.57833164328119e-01 - 2.16817353069425e-01 1.59188793369321e-01 - 2.29396483963478e-01 1.60249491178254e-01 - 2.42377800694080e-01 1.61037466418900e-01 - 2.55773624268338e-01 1.61527990576809e-01 - 2.69566785632899e-01 1.61725592072508e-01 - 2.83765797226135e-01 1.61628572129705e-01 - 2.98347982887804e-01 1.61227616225551e-01 - 3.13318978785268e-01 1.60529134419846e-01 - 3.28658461892810e-01 1.59546972615705e-01 - 3.44364941645546e-01 1.58268437383844e-01 - 3.60419773725681e-01 1.56707380674239e-01 - 3.76811233766957e-01 1.54853953979771e-01 - 3.93525251020729e-01 1.52724228613081e-01 - 4.10538642553571e-01 1.50327802191204e-01 - 4.27843232490823e-01 1.47663230706415e-01 - 4.45406663468198e-01 1.44754671975603e-01 - 4.63222254103030e-01 1.41610096015018e-01 - 4.81251545655716e-01 1.38233693464268e-01 - 4.99481026671737e-01 1.34653643905950e-01 - 5.17879583085697e-01 1.30897588823569e-01 - 5.36417631367010e-01 1.26978714388034e-01 - 5.55075704909560e-01 1.22913591230606e-01 - 5.73808427242608e-01 1.18721456482138e-01 - 5.92596731105059e-01 1.14407007262747e-01 - 6.11401377553511e-01 1.09997724386190e-01 - 6.30186430605241e-01 1.05502247754470e-01 - 6.48926781663159e-01 1.00945308262218e-01 - 6.67570206424973e-01 9.63375060374201e-02 - 6.86088429590952e-01 9.17003095592600e-02 - 7.04445389043917e-01 8.70515744418953e-02 - 7.22592093722966e-01 8.24038830818072e-02 - 7.40501800453524e-01 7.77734757398223e-02 - 7.58125457122835e-01 7.31915846012941e-02 - 7.75421014376153e-01 6.86732005713782e-02 - 7.92362373587600e-01 6.42388715780745e-02 - 8.08894546151696e-01 5.99112120918192e-02 - 8.24974633014891e-01 5.56826479691993e-02 - 8.40576952273409e-01 5.15856595464641e-02 - 8.55652758808818e-01 4.76475488773555e-02 - 8.70162898882712e-01 4.38686620047300e-02 - 8.84085033071272e-01 4.02674474797666e-02 - 8.97361214262371e-01 3.68438469736901e-02 - 9.09954680076662e-01 3.36218605191145e-02 - 9.21851471402547e-01 3.06047412392211e-02 - 9.33012836658427e-01 2.78108377031037e-02 - 9.43389278969050e-01 2.52359220576833e-02 - 9.52973153850560e-01 2.28644364225864e-02 - 9.61743130827061e-01 2.07008529631347e-02 - 9.69640690675464e-01 1.87495279101514e-02 - 9.76664215898664e-01 1.70025122680530e-02 - 9.82815077112014e-01 1.54686422783100e-02 - 9.88028440045103e-01 1.41623841538989e-02 - 9.92304836603751e-01 1.30902233686081e-02 - 9.95693518775914e-01 1.22423578114465e-02 - 9.98120489340015e-01 1.16192185402651e-02 - 9.99443037908705e-01 1.12692437532816e-02 - 1.00000000000000e+00 1.11557580876974e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_18.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_18.dat index aa73a9c7..46a1237d 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_18.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_18.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_18_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF18_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF18_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.729876 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-11.426944 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.763146 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -0.990112 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.958095 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.178812 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.011807 Cd0 ! 2D drag coefficient value at 0-lift. - -0.086043 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.013340 Cd0 ! 2D drag coefficient value at 0-lift. +-0.084934 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 5.07007184615326e-03 2.86325698794117e-02 4.87628184221038e-03 --1.77714285740401e+02 6.88416029369718e-02 3.29815908979737e-02 9.14675940442329e-02 --1.75428571400002e+02 1.39083021351538e-01 3.24680129594405e-02 1.82723591463010e-01 --1.73142857116900e+02 2.06514790833493e-01 3.11975613020155e-02 2.74608231066447e-01 --1.70857160423602e+02 2.72086183275065e-01 3.40283190491494e-02 3.65179592622244e-01 --1.68571631778825e+02 3.36900918146798e-01 4.44187183887991e-02 4.02897200584883e-01 --1.66285714267592e+02 4.02215150624318e-01 6.20774563266668e-02 4.06497608538193e-01 --1.63999999984490e+02 4.69233266766961e-01 8.53801298919622e-02 4.09580175239176e-01 --1.61714472886699e+02 5.39143983966078e-01 1.13461108244481e-01 4.14807479975634e-01 --1.59428371284127e+02 6.12375466889276e-01 1.45469170554651e-01 4.21104894833768e-01 --1.57142842639350e+02 6.86443396901142e-01 1.80938855673554e-01 4.38285344173611e-01 --1.54857313994574e+02 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0.00000000000000e+00 2.92816357990909e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_18_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_18_Coords.txt deleted file mode 100644 index beae584f..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_18_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.303738 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -1.15973289566072e-02 - 9.99429683992583e-01 -1.14468349764518e-02 - 9.98063017832965e-01 -1.10899803118504e-02 - 9.95573914266674e-01 -1.04539395162703e-02 - 9.92086309749559e-01 -9.59368121087690e-03 - 9.87686148675057e-01 -8.55292683081155e-03 - 9.82330525170640e-01 -7.37725191998046e-03 - 9.76011908335692e-01 -6.13658086684056e-03 - 9.68787467298381e-01 -4.91215926386993e-03 - 9.60674860259240e-01 -3.77989326550799e-03 - 9.51675358763677e-01 -2.65758688752549e-03 - 9.41827652746244e-01 -1.79874338234190e-03 - 9.31175295355131e-01 -1.19715469085257e-03 - 9.19730397431178e-01 -8.69944237594205e-04 - 9.07524559194720e-01 -8.78707636721251e-04 - 8.94610408070308e-01 -1.26029493380436e-03 - 8.81009696499435e-01 -2.10041025063212e-03 - 8.66747905197194e-01 -3.43437570555784e-03 - 8.51890258171205e-01 -5.29300806087939e-03 - 8.36469462621421e-01 -7.70263601194727e-03 - 8.20513485943698e-01 -1.06654133596987e-02 - 8.04073832217581e-01 -1.42070558746366e-02 - 7.87191529885653e-01 -1.83252942812443e-02 - 7.69897919101553e-01 -2.30705972538142e-02 - 7.52252341235159e-01 -2.84073997620480e-02 - 7.34291349178558e-01 -3.42815196310205e-02 - 7.16044924955764e-01 -4.06441849828613e-02 - 6.97571640033109e-01 -4.74398840793077e-02 - 6.78906186433687e-01 -5.46116925413902e-02 - 6.60080312620540e-01 -6.20502754302341e-02 - 6.41147517137212e-01 -6.96599324999407e-02 - 6.22137650968852e-01 -7.73477002299955e-02 - 6.03087998194415e-01 -8.50219353467436e-02 - 5.84045042118975e-01 -9.25985927100597e-02 - 5.65030897687003e-01 -9.99728938310690e-02 - 5.46088602779599e-01 -1.07082604774240e-01 - 5.27248673916899e-01 -1.13849184865199e-01 - 5.08535950506088e-01 -1.20232541192611e-01 - 4.89992355470388e-01 -1.26194656331177e-01 - 4.71632114506831e-01 -1.31704870832856e-01 - 4.53492503744347e-01 -1.36729064136422e-01 - 4.35593302897673e-01 -1.41253784361482e-01 - 4.17956065616942e-01 -1.45271650618195e-01 - 4.00609748442576e-01 -1.48780240787823e-01 - 3.83560931606009e-01 -1.51791109770454e-01 - 3.66843215733716e-01 -1.54312077045387e-01 - 3.50457316320503e-01 -1.56356150935547e-01 - 3.34434484008630e-01 -1.57945495730877e-01 - 3.18774100329315e-01 -1.59089026352254e-01 - 3.03499623121295e-01 -1.59809661411791e-01 - 2.88611293565648e-01 -1.60127690676097e-01 - 2.74124386665666e-01 -1.60051906530284e-01 - 2.60041455523719e-01 -1.59601496413048e-01 - 2.46374872015917e-01 -1.58800980631567e-01 - 2.33123443938834e-01 -1.57672245983227e-01 - 2.20293777810423e-01 -1.56228153230862e-01 - 2.07883282965331e-01 -1.54487081855267e-01 - 1.95902956391646e-01 -1.52477324467629e-01 - 1.84341253066628e-01 -1.50207266536766e-01 - 1.73213930954160e-01 -1.47708456457197e-01 - 1.62499176129638e-01 -1.44984770175758e-01 - 1.52214602777260e-01 -1.42050773104928e-01 - 1.42331759398971e-01 -1.38932848400858e-01 - 1.32872111539190e-01 -1.35644633063185e-01 - 1.23806439629760e-01 -1.32198180251802e-01 - 1.15147623386077e-01 -1.28627161592124e-01 - 1.06887208802748e-01 -1.24930875780421e-01 - 9.90071115215634e-02 -1.21125308775438e-01 - 9.15234043853439e-02 -1.17232966388533e-01 - 8.43970428172224e-02 -1.13251725110613e-01 - 7.76464790199521e-02 -1.09204709368849e-01 - 7.12479082120209e-02 -1.05105103679582e-01 - 6.51878662973747e-02 -1.00953934114211e-01 - 5.94874721274202e-02 -9.67848467301050e-02 - 5.41002464180900e-02 -9.25981813416382e-02 - 4.90378786701877e-02 -8.84118024478169e-02 - 4.43003497573338e-02 -8.42342768224228e-02 - 3.98423597346806e-02 -8.00436602957583e-02 - 3.56899752436130e-02 -7.58855586500531e-02 - 3.18292350050658e-02 -7.17617940202580e-02 - 2.82200072057899e-02 -6.76418796528754e-02 - 2.48925247792699e-02 -6.35678284078582e-02 - 2.18286683030034e-02 -5.95507751501638e-02 - 1.89846947131331e-02 -5.55564312915758e-02 - 1.63921917020335e-02 -5.16530246815200e-02 - 1.40446346341990e-02 -4.78505057459223e-02 - 1.18798249846349e-02 -4.40482368698709e-02 - 9.93094518736223e-03 -4.03377120947413e-02 - 8.21940795734749e-03 -3.67061390593434e-02 - 6.65838622137879e-03 -3.30221934852819e-02 - 5.26774192850643e-03 -2.93241000935553e-02 - 4.09515753852961e-03 -2.57511764881335e-02 - 3.09878859713640e-03 -2.22525377995310e-02 - 2.19660773551101e-03 -1.85676682221469e-02 - 1.46264176301869e-03 -1.49627868834444e-02 - 9.64484608297914e-04 -1.21196875805388e-02 - 5.99373867982851e-04 -9.07234393790360e-03 - 2.90086645599082e-04 -5.02490911456242e-03 - 7.80707788302466e-05 -1.28597940606798e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.24843700938023e-03 - 2.89878724192004e-04 4.76096789641785e-03 - 5.98775316682048e-04 8.93725137962992e-03 - 9.63326351634835e-04 1.21200601013893e-02 - 1.45966821282819e-03 1.50680015132228e-02 - 2.19097636449990e-03 1.87900849828002e-02 - 3.08997841959778e-03 2.25985530850654e-02 - 4.08271112470316e-03 2.63602545915558e-02 - 5.24853124383664e-03 3.02600830471717e-02 - 6.63128223001261e-03 3.42089225061911e-02 - 8.18368429859057e-03 3.81256789800804e-02 - 9.88361416849065e-03 4.19162176477322e-02 - 1.18176401547236e-02 4.57725899625453e-02 - 1.39661993216829e-02 4.97219619286037e-02 - 1.62951420791042e-02 5.36554009826543e-02 - 1.88631937781153e-02 5.76852782753790e-02 - 2.16807137532775e-02 6.17965947427903e-02 - 2.47159162958630e-02 6.59200633604614e-02 - 2.80064400105862e-02 7.00916703354257e-02 - 3.15762558914965e-02 7.43029861053786e-02 - 3.53948396168776e-02 7.85018174507752e-02 - 3.94949825480075e-02 8.27148939614041e-02 - 4.38979282781582e-02 8.69567334477698e-02 - 4.85758075737765e-02 9.11812058787134e-02 - 5.35679916138119e-02 9.53949572133078e-02 - 5.88818211488708e-02 9.95996253998170e-02 - 6.45001629027312e-02 1.03749363067426e-01 - 7.04692046391145e-02 1.07866177499883e-01 - 7.67740309924711e-02 1.11921670420955e-01 - 8.34162127168367e-02 1.15894994075347e-01 - 9.04290195190654e-02 1.19782394841940e-01 - 9.77906533229447e-02 1.23565900091282e-01 - 1.05536187198748e-01 1.27240882283450e-01 - 1.13658760041779e-01 1.30779587555972e-01 - 1.22161483318940e-01 1.34163928735883e-01 - 1.31067498602735e-01 1.37390163866224e-01 - 1.40354649921884e-01 1.40443504871700e-01 - 1.50055110786138e-01 1.43308641297507e-01 - 1.60148962661562e-01 1.45969631470955e-01 - 1.70658187899640e-01 1.48394280626455e-01 - 1.81574957422924e-01 1.50583684713674e-01 - 1.92907571409635e-01 1.52521565631870e-01 - 2.04657634577812e-01 1.54185275739136e-01 - 2.16817353069425e-01 1.55582767945564e-01 - 2.29396483963478e-01 1.56691944460491e-01 - 2.42377800694080e-01 1.57529719945299e-01 - 2.55773624268338e-01 1.58076798601446e-01 - 2.69566785632899e-01 1.58334555243700e-01 - 2.83765797226135e-01 1.58296189265822e-01 - 2.98347982887804e-01 1.57963559314878e-01 - 3.13318978785268e-01 1.57331569364315e-01 - 3.28658461892810e-01 1.56417383111704e-01 - 3.44364941645546e-01 1.55215105664807e-01 - 3.60419773725681e-01 1.53731612853514e-01 - 3.76811233766957e-01 1.51959776289306e-01 - 3.93525251020729e-01 1.49917352708199e-01 - 4.10538642553571e-01 1.47605354036027e-01 - 4.27843232490823e-01 1.45031949597507e-01 - 4.45406663468198e-01 1.42215359411962e-01 - 4.63222254103030e-01 1.39164717721414e-01 - 4.81251545655716e-01 1.35881392998299e-01 - 4.99481026671737e-01 1.32395495482445e-01 - 5.17879583085697e-01 1.28727188034270e-01 - 5.36417631367010e-01 1.24897299511965e-01 - 5.55075704909560e-01 1.20923050141640e-01 - 5.73808427242608e-01 1.16816237247672e-01 - 5.92596731105059e-01 1.12585603900550e-01 - 6.11401377553511e-01 1.08258160024038e-01 - 6.30186430605241e-01 1.03841531488075e-01 - 6.48926781663159e-01 9.93605721664613e-02 - 6.67570206424973e-01 9.48252512870579e-02 - 6.86088429590952e-01 9.02537365804535e-02 - 7.04445389043917e-01 8.56706832233751e-02 - 7.22592093722966e-01 8.10823659958134e-02 - 7.40501800453524e-01 7.65093989552019e-02 - 7.58125457122835e-01 7.19819118507500e-02 - 7.75421014376153e-01 6.75156454632159e-02 - 7.92362373587600e-01 6.31317074093705e-02 - 8.08894546151696e-01 5.88513562196451e-02 - 8.24974633014891e-01 5.46689032424792e-02 - 8.40576952273409e-01 5.06181239461534e-02 - 8.55652758808818e-01 4.67212421268558e-02 - 8.70162898882712e-01 4.29849668110092e-02 - 8.84085033071272e-01 3.94240147655494e-02 - 8.97361214262371e-01 3.60409807959559e-02 - 9.09954680076662e-01 3.28574061081271e-02 - 9.21851471402547e-01 2.98775961664988e-02 - 9.33012836658427e-01 2.71188684920361e-02 - 9.43389278969050e-01 2.45768366699642e-02 - 9.52973153850560e-01 2.22368741539826e-02 - 9.61743130827061e-01 2.01021567220506e-02 - 9.69640690675464e-01 1.81793775868964e-02 - 9.76664215898664e-01 1.64616976751913e-02 - 9.82815077112014e-01 1.49555546855250e-02 - 9.88028440045103e-01 1.36754640477392e-02 - 9.92304836603751e-01 1.26257872889606e-02 - 9.95693518775914e-01 1.17959186890833e-02 - 9.98120489340015e-01 1.11533617483310e-02 - 9.99443037908705e-01 1.08120282774804e-02 - 1.00000000000000e+00 1.07112879742080e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_19.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_19.dat index ad51c8cc..a02be4c0 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_19.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_19.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_19_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF19_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF19_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.691772 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-11.818551 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.748678 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.004001 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.950200 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.146200 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.011450 Cd0 ! 2D drag coefficient value at 0-lift. - -0.086141 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.012928 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085215 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 6.37313505100223e-03 2.70399640359817e-02 4.89071502011557e-03 --1.77714285740401e+02 6.79987817472275e-02 3.12941222643822e-02 9.14881064210027e-02 --1.75428571400002e+02 1.37295388184459e-01 3.09003960890030e-02 1.82663620683623e-01 --1.73142857116900e+02 2.03709858862760e-01 2.99708613232587e-02 2.74694913460182e-01 --1.70857160423602e+02 2.68165532841372e-01 3.31402827184829e-02 3.65130691458951e-01 --1.68571631778825e+02 3.31810674098875e-01 4.38116840886545e-02 4.02349005307118e-01 --1.66285714267592e+02 3.96003705364937e-01 6.16918051024907e-02 4.05194560003816e-01 --1.63999999984490e+02 4.62043605519726e-01 8.52948969739735e-02 4.07340992772470e-01 --1.61714472886699e+02 5.31198997821832e-01 1.13646900588712e-01 4.11734906099602e-01 --1.59428371284127e+02 6.03883711466990e-01 1.45837642133393e-01 4.17443005512844e-01 --1.57142842639350e+02 6.77350666223579e-01 1.81411732271765e-01 4.34433375672721e-01 --1.54857313994574e+02 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0.00000000000000e+00 2.80270148732245e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_19_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_19_Coords.txt deleted file mode 100644 index 5d1582e1..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_19_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.300956 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -1.07492461607641e-02 - 9.99429683992583e-01 -1.06068094512453e-02 - 9.98063017832965e-01 -1.02692930759833e-02 - 9.95573914266674e-01 -9.66846302384462e-03 - 9.92086309749559e-01 -8.85711735343728e-03 - 9.87686148675057e-01 -7.87967265492259e-03 - 9.82330525170640e-01 -6.77330527815946e-03 - 9.76011908335692e-01 -5.59605513334143e-03 - 9.68787467298381e-01 -4.41963980734353e-03 - 9.60674860259240e-01 -3.31175065239411e-03 - 9.51675358763677e-01 -2.23430303435544e-03 - 9.41827652746244e-01 -1.37573864005009e-03 - 9.31175295355131e-01 -7.70395596784982e-04 - 9.19730397431178e-01 -4.35625899563849e-04 - 9.07524559194720e-01 -4.29951332845528e-04 - 8.94610408070308e-01 -7.84352226961512e-04 - 8.81009696499435e-01 -1.59449920194081e-03 - 8.66747905197194e-01 -2.89072565504418e-03 - 8.51890258171205e-01 -4.70142107110454e-03 - 8.36469462621421e-01 -7.04942634202232e-03 - 8.20513485943698e-01 -9.94568749736675e-03 - 8.04073832217581e-01 -1.34125326420967e-02 - 7.87191529885653e-01 -1.74530045492906e-02 - 7.69897919101553e-01 -2.21206868705089e-02 - 7.52252341235159e-01 -2.73792677621921e-02 - 7.34291349178558e-01 -3.31683732874198e-02 - 7.16044924955764e-01 -3.94451601994509e-02 - 6.97571640033109e-01 -4.61587483189008e-02 - 6.78906186433687e-01 -5.32482936428680e-02 - 6.60080312620540e-01 -6.06134436017240e-02 - 6.41147517137212e-01 -6.81543968021725e-02 - 6.22137650968852e-01 -7.57810246923034e-02 - 6.03087998194415e-01 -8.34004766812860e-02 - 5.84045042118975e-01 -9.09180603055268e-02 - 5.65030897687003e-01 -9.82392041128300e-02 - 5.46088602779599e-01 -1.05297229710443e-01 - 5.27248673916899e-01 -1.12012028949945e-01 - 5.08535950506088e-01 -1.18343656761465e-01 - 4.89992355470388e-01 -1.24252371181680e-01 - 4.71632114506831e-01 -1.29705815905370e-01 - 4.53492503744347e-01 -1.34671288756764e-01 - 4.35593302897673e-01 -1.39139069418005e-01 - 4.17956065616942e-01 -1.43105469041802e-01 - 4.00609748442576e-01 -1.46566588720666e-01 - 3.83560931606009e-01 -1.49529645715835e-01 - 3.66843215733716e-01 -1.52008932070576e-01 - 3.50457316320503e-01 -1.54010750932811e-01 - 3.34434484008630e-01 -1.55558327598359e-01 - 3.18774100329315e-01 -1.56659739070217e-01 - 3.03499623121295e-01 -1.57343529071545e-01 - 2.88611293565648e-01 -1.57621488292395e-01 - 2.74124386665666e-01 -1.57511858448276e-01 - 2.60041455523719e-01 -1.57023871360149e-01 - 2.46374872015917e-01 -1.56192167145598e-01 - 2.33123443938834e-01 -1.55030009917439e-01 - 2.20293777810423e-01 -1.53552797258517e-01 - 2.07883282965331e-01 -1.51780718070517e-01 - 1.95902956391646e-01 -1.49737545204788e-01 - 1.84341253066628e-01 -1.47434386106696e-01 - 1.73213930954160e-01 -1.44900382361602e-01 - 1.62499176129638e-01 -1.42139008214321e-01 - 1.52214602777260e-01 -1.39168965708357e-01 - 1.42331759398971e-01 -1.36016422517681e-01 - 1.32872111539190e-01 -1.32696277248013e-01 - 1.23806439629760e-01 -1.29218194343020e-01 - 1.15147623386077e-01 -1.25617546455611e-01 - 1.06887208802748e-01 -1.21896745936352e-01 - 9.90071115215634e-02 -1.18069218866786e-01 - 9.15234043853439e-02 -1.14163581591374e-01 - 8.43970428172224e-02 -1.10178231277952e-01 - 7.76464790199521e-02 -1.06135840518403e-01 - 7.12479082120209e-02 -1.02052736163078e-01 - 6.51878662973747e-02 -9.79285137741641e-02 - 5.94874721274202e-02 -9.37963407622562e-02 - 5.41002464180900e-02 -8.96555571476290e-02 - 4.90378786701877e-02 -8.55214827111920e-02 - 4.43003497573338e-02 -8.14030769871039e-02 - 3.98423597346806e-02 -7.72824617012249e-02 - 3.56899752436130e-02 -7.32047262741267e-02 - 3.18292350050658e-02 -6.91718232269760e-02 - 2.82200072057899e-02 -6.51574979936013e-02 - 2.48925247792699e-02 -6.11977880078864e-02 - 2.18286683030034e-02 -5.73047010062414e-02 - 1.89846947131331e-02 -5.34328136117668e-02 - 1.63921917020335e-02 -4.96550719407382e-02 - 1.40446346341990e-02 -4.59711471430950e-02 - 1.18798249846349e-02 -4.22929665305905e-02 - 9.93094518736223e-03 -3.87126295217846e-02 - 8.21940795734749e-03 -3.52192347547890e-02 - 6.65838622137879e-03 -3.16907602303729e-02 - 5.26774192850643e-03 -2.81720825263415e-02 - 4.09515753852961e-03 -2.47669671212900e-02 - 3.09878859713640e-03 -2.14690650790342e-02 - 2.19660773551101e-03 -1.80671778392112e-02 - 1.46264176301869e-03 -1.46191048061870e-02 - 9.64484608297914e-04 -1.17943263830112e-02 - 5.99373867982851e-04 -8.66124024823033e-03 - 2.90086645599082e-04 -4.57219930874803e-03 - 7.80707788302466e-05 -1.16821656725171e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.14197761651511e-03 - 2.89878724192004e-04 4.38771720193327e-03 - 5.98775316682048e-04 8.62150393673867e-03 - 9.63326351634835e-04 1.19420305507577e-02 - 1.45966821282819e-03 1.48984877502186e-02 - 2.19097636449990e-03 1.84457662947963e-02 - 3.08997841959778e-03 2.19484194861812e-02 - 4.08271112470316e-03 2.54792194815247e-02 - 5.24853124383664e-03 2.91200192103009e-02 - 6.63128223001261e-03 3.28373128266105e-02 - 8.18368429859057e-03 3.65855464348137e-02 - 9.88361416849065e-03 4.02367338580041e-02 - 1.18176401547236e-02 4.39749160532656e-02 - 1.39661993216829e-02 4.78109558280905e-02 - 1.62951420791042e-02 5.16292143445625e-02 - 1.88631937781153e-02 5.55412068552128e-02 - 2.16807137532775e-02 5.95307165622953e-02 - 2.47159162958630e-02 6.35317282549699e-02 - 2.80064400105862e-02 6.75810642994221e-02 - 3.15762558914965e-02 7.16690940845782e-02 - 3.53948396168776e-02 7.57500300984636e-02 - 3.94949825480075e-02 7.98508819808669e-02 - 4.38979282781582e-02 8.39856797114797e-02 - 4.85758075737765e-02 8.81097234101234e-02 - 5.35679916138119e-02 9.22332278641986e-02 - 5.88818211488708e-02 9.63490778620983e-02 - 6.45001629027312e-02 1.00418272431663e-01 - 7.04692046391145e-02 1.04463856156596e-01 - 7.67740309924711e-02 1.08457701365447e-01 - 8.34162127168367e-02 1.12380326767273e-01 - 9.04290195190654e-02 1.16225632011226e-01 - 9.77906533229447e-02 1.19975231347666e-01 - 1.05536187198748e-01 1.23624100375505e-01 - 1.13658760041779e-01 1.27141946731322e-01 - 1.22161483318940e-01 1.30518843661499e-01 - 1.31067498602735e-01 1.33743051527760e-01 - 1.40354649921884e-01 1.36800176932950e-01 - 1.50055110786138e-01 1.39673682162572e-01 - 1.60148962661562e-01 1.42349489670671e-01 - 1.70658187899640e-01 1.44800218531333e-01 - 1.81574957422924e-01 1.47019297924366e-01 - 1.92907571409635e-01 1.48989405268507e-01 - 2.04657634577812e-01 1.50697257627368e-01 - 2.16817353069425e-01 1.52138768539404e-01 - 2.29396483963478e-01 1.53299478586317e-01 - 2.42377800694080e-01 1.54189567750055e-01 - 2.55773624268338e-01 1.54796068268135e-01 - 2.69566785632899e-01 1.55116334936720e-01 - 2.83765797226135e-01 1.55139018280801e-01 - 2.98347982887804e-01 1.54877096553580e-01 - 3.13318978785268e-01 1.54313575995049e-01 - 3.28658461892810e-01 1.53468435741006e-01 - 3.44364941645546e-01 1.52342887263364e-01 - 3.60419773725681e-01 1.50936861712876e-01 - 3.76811233766957e-01 1.49246343239583e-01 - 3.93525251020729e-01 1.47290435984281e-01 - 4.10538642553571e-01 1.45061115180754e-01 - 4.27843232490823e-01 1.42577065738483e-01 - 4.45406663468198e-01 1.39849811158926e-01 - 4.63222254103030e-01 1.36890173508441e-01 - 4.81251545655716e-01 1.33696590831028e-01 - 4.99481026671737e-01 1.30301057974167e-01 - 5.17879583085697e-01 1.26715829798083e-01 - 5.36417631367010e-01 1.22969747635201e-01 - 5.55075704909560e-01 1.19080822574934e-01 - 5.73808427242608e-01 1.15053186756262e-01 - 5.92596731105059e-01 1.10900292697299e-01 - 6.11401377553511e-01 1.06648408497278e-01 - 6.30186430605241e-01 1.02304247736944e-01 - 6.48926781663159e-01 9.78927844394580e-02 - 6.67570206424973e-01 9.34240648744466e-02 - 6.86088429590952e-01 8.89123593352927e-02 - 7.04445389043917e-01 8.43891295443049e-02 - 7.22592093722966e-01 7.98548687487617e-02 - 7.40501800453524e-01 7.53341256769165e-02 - 7.58125457122835e-01 7.08561275141062e-02 - 7.75421014376153e-01 6.64370387944605e-02 - 7.92362373587600e-01 6.20984479350926e-02 - 8.08894546151696e-01 5.78600546009995e-02 - 8.24974633014891e-01 5.37190660498846e-02 - 8.40576952273409e-01 4.97099064137008e-02 - 8.55652758808818e-01 4.58488680696058e-02 - 8.70162898882712e-01 4.21500865944395e-02 - 8.84085033071272e-01 3.86236366876970e-02 - 8.97361214262371e-01 3.52755417282350e-02 - 9.09954680076662e-01 3.21244352428996e-02 - 9.21851471402547e-01 2.91759347450359e-02 - 9.33012836658427e-01 2.64457771696264e-02 - 9.43389278969050e-01 2.39289879904336e-02 - 9.52973153850560e-01 2.16115107045570e-02 - 9.61743130827061e-01 1.94958821519455e-02 - 9.69640690675464e-01 1.75918884008948e-02 - 9.76664215898664e-01 1.58947834775884e-02 - 9.82815077112014e-01 1.44081242609840e-02 - 9.88028440045103e-01 1.31469144530348e-02 - 9.92304836603751e-01 1.21131742129248e-02 - 9.95693518775914e-01 1.12954928541740e-02 - 9.98120489340015e-01 1.06266557589495e-02 - 9.99443037908705e-01 1.03004014284040e-02 - 1.00000000000000e+00 1.02029672468964e-02 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_20.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_20.dat index 60ef459e..31ceaebf 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_20.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_20.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_20_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF20_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF20_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.662894 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.025354 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.731335 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.015286 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.944572 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.115998 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.011076 Cd0 ! 2D drag coefficient value at 0-lift. - -0.086166 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.012519 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085427 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 7.48851227400723e-03 2.53858986069414e-02 4.90313077894166e-03 --1.77714285740401e+02 6.73190902780762e-02 2.94951534041631e-02 9.15056643090266e-02 --1.75428571400002e+02 1.35854167099975e-01 2.92525865367176e-02 1.82612287761992e-01 --1.73142857116900e+02 2.01175704089417e-01 2.86992181539527e-02 2.74769110603689e-01 --1.70857160423602e+02 2.64368460847040e-01 3.22158223702534e-02 3.65088833747435e-01 --1.68571631778825e+02 3.26720459608804e-01 4.31634961011352e-02 4.01764174977197e-01 --1.66285714267592e+02 3.89710992069428e-01 6.12560542443807e-02 4.03806140753702e-01 --1.63999999984490e+02 4.54763279458331e-01 8.51941024916883e-02 4.04995026131900e-01 --1.61714472886699e+02 5.23274252436907e-01 1.13864079326688e-01 4.08466762964897e-01 --1.59428371284127e+02 5.95703931264948e-01 1.46279856652537e-01 4.13581635440592e-01 --1.57142842639350e+02 6.68984017864372e-01 1.81991924493031e-01 4.30402553840922e-01 --1.54857313994574e+02 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0.00000000000000e+00 2.67292776565803e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_20_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_20_Coords.txt deleted file mode 100644 index 39da0506..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_20_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.298005 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -9.87102262426032e-03 - 9.99429683992583e-01 -9.73715493894287e-03 - 9.98063017832965e-01 -9.42013068282464e-03 - 9.95573914266674e-01 -8.85636411198811e-03 - 9.92086309749559e-01 -8.09604184609199e-03 - 9.87686148675057e-01 -7.18377747041872e-03 - 9.82330525170640e-01 -6.14877507497999e-03 - 9.76011908335692e-01 -5.03748716239816e-03 - 9.68787467298381e-01 -3.91172562794235e-03 - 9.60674860259240e-01 -2.82994994340167e-03 - 9.51675358763677e-01 -1.81170970584490e-03 - 9.41827652746244e-01 -9.58161147185984e-04 - 9.31175295355131e-01 -3.49992486825688e-04 - 9.19730397431178e-01 -7.59523701763468e-06 - 9.07524559194720e-01 1.45051510283326e-05 - 8.94610408070308e-01 -3.10800792999515e-04 - 8.81009696499435e-01 -1.08838168939843e-03 - 8.66747905197194e-01 -2.34388373920215e-03 - 8.51890258171205e-01 -4.10314373885626e-03 - 8.36469462621421e-01 -6.38592494172068e-03 - 8.20513485943698e-01 -9.21150488868295e-03 - 8.04073832217581e-01 -1.25991810248407e-02 - 7.87191529885653e-01 -1.65575885945664e-02 - 7.69897919101553e-01 -2.11429881474676e-02 - 7.52252341235159e-01 -2.63187374069883e-02 - 7.34291349178558e-01 -3.20188819166251e-02 - 7.16044924955764e-01 -3.82061231319408e-02 - 6.97571640033109e-01 -4.48336602735858e-02 - 6.78906186433687e-01 -5.18371388563992e-02 - 6.60080312620540e-01 -5.91249020867967e-02 - 6.41147517137212e-01 -6.65934615886315e-02 - 6.22137650968852e-01 -7.41551627396938e-02 - 6.03087998194415e-01 -8.17157810396993e-02 - 5.84045042118975e-01 -8.91707985864750e-02 - 5.65030897687003e-01 -9.64351542498274e-02 - 5.46088602779599e-01 -1.03437923402534e-01 - 5.27248673916899e-01 -1.10097774292014e-01 - 5.08535950506088e-01 -1.16374851107650e-01 - 4.89992355470388e-01 -1.22227295127162e-01 - 4.71632114506831e-01 -1.27621321054695e-01 - 4.53492503744347e-01 -1.32525867098173e-01 - 4.35593302897673e-01 -1.36934474718021e-01 - 4.17956065616942e-01 -1.40846732275920e-01 - 4.00609748442576e-01 -1.44257864953687e-01 - 3.83560931606009e-01 -1.47170607116299e-01 - 3.66843215733716e-01 -1.49605545206638e-01 - 3.50457316320503e-01 -1.51562723538508e-01 - 3.34434484008630e-01 -1.53066347081126e-01 - 3.18774100329315e-01 -1.54123984765028e-01 - 3.03499623121295e-01 -1.54768981696423e-01 - 2.88611293565648e-01 -1.55005688532638e-01 - 2.74124386665666e-01 -1.54860890574391e-01 - 2.60041455523719e-01 -1.54334938675961e-01 - 2.46374872015917e-01 -1.53471463393573e-01 - 2.33123443938834e-01 -1.52276021302275e-01 - 2.20293777810423e-01 -1.50766117114406e-01 - 2.07883282965331e-01 -1.48964004988437e-01 - 1.95902956391646e-01 -1.46888922418505e-01 - 1.84341253066628e-01 -1.44554586959506e-01 - 1.73213930954160e-01 -1.41987825411878e-01 - 1.62499176129638e-01 -1.39192176441612e-01 - 1.52214602777260e-01 -1.36190271753258e-01 - 1.42331759398971e-01 -1.33007702707641e-01 - 1.32872111539190e-01 -1.29660657924939e-01 - 1.23806439629760e-01 -1.26156884952740e-01 - 1.15147623386077e-01 -1.22532693239468e-01 - 1.06887208802748e-01 -1.18794091237399e-01 - 9.90071115215634e-02 -1.14951890571067e-01 - 9.15234043853439e-02 -1.11040565927726e-01 - 8.43970428172224e-02 -1.07058304446559e-01 - 7.76464790199521e-02 -1.03027935533350e-01 - 7.12479082120209e-02 -9.89677927500959e-02 - 6.51878662973747e-02 -9.48766608120193e-02 - 5.94874721274202e-02 -9.07868453494851e-02 - 5.41002464180900e-02 -8.66965542520504e-02 - 4.90378786701877e-02 -8.26195876753088e-02 - 4.43003497573338e-02 -7.85664459118022e-02 - 3.98423597346806e-02 -7.45217625538126e-02 - 3.56899752436130e-02 -7.05295895396832e-02 - 3.18292350050658e-02 -6.65918765263020e-02 - 2.82200072057899e-02 -6.26859135070649e-02 - 2.48925247792699e-02 -5.88426397649799e-02 - 2.18286683030034e-02 -5.50740325512403e-02 - 1.89846947131331e-02 -5.13251282685158e-02 - 1.63921917020335e-02 -4.76729557776380e-02 - 1.40446346341990e-02 -4.41092859461254e-02 - 1.18798249846349e-02 -4.05557584023979e-02 - 9.93094518736223e-03 -3.71045207374667e-02 - 8.21940795734749e-03 -3.37485757930770e-02 - 6.65838622137879e-03 -3.03730596796264e-02 - 5.26774192850643e-03 -2.70300219611843e-02 - 4.09515753852961e-03 -2.37892045180150e-02 - 3.09878859713640e-03 -2.06842154767480e-02 - 2.19660773551101e-03 -1.75593966483925e-02 - 1.46264176301869e-03 -1.42781571172725e-02 - 9.64484608297914e-04 -1.14756021448839e-02 - 5.99373867982851e-04 -8.25990591860449e-03 - 2.90086645599082e-04 -4.14685396698059e-03 - 7.80707788302466e-05 -1.05743821324451e-03 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 1.04612486130181e-03 - 2.89878724192004e-04 4.07186807157397e-03 - 5.98775316682048e-04 8.33393560966345e-03 - 9.63326351634835e-04 1.17287890345193e-02 - 1.45966821282819e-03 1.46849401862812e-02 - 2.19097636449990e-03 1.80690106399829e-02 - 3.08997841959778e-03 2.13189238035003e-02 - 4.08271112470316e-03 2.46508158175100e-02 - 5.24853124383664e-03 2.80569853581374e-02 - 6.63128223001261e-03 3.15626596420180e-02 - 8.18368429859057e-03 3.51456100718470e-02 - 9.88361416849065e-03 3.86588664733750e-02 - 1.18176401547236e-02 4.22809779123850e-02 - 1.39661993216829e-02 4.60039734926984e-02 - 1.62951420791042e-02 4.97094140215597e-02 - 1.88631937781153e-02 5.35056175784563e-02 - 2.16807137532775e-02 5.73749322764474e-02 - 2.47159162958630e-02 6.12545641937899e-02 - 2.80064400105862e-02 6.51814623204659e-02 - 3.15762558914965e-02 6.91497435715482e-02 - 3.53948396168776e-02 7.31195687645608e-02 - 3.94949825480075e-02 7.71143585145346e-02 - 4.38979282781582e-02 8.11467824025788e-02 - 4.85758075737765e-02 8.51727966790286e-02 - 5.35679916138119e-02 8.92071165426950e-02 - 5.88818211488708e-02 9.32347156669188e-02 - 6.45001629027312e-02 9.72230649710512e-02 - 7.04692046391145e-02 1.01195874217438e-01 - 7.67740309924711e-02 1.05125213350687e-01 - 8.34162127168367e-02 1.08993655448086e-01 - 9.04290195190654e-02 1.12792768488719e-01 - 9.77906533229447e-02 1.16504032087154e-01 - 1.05536187198748e-01 1.20121665218296e-01 - 1.13658760041779e-01 1.23614030741803e-01 - 1.22161483318940e-01 1.26978356584806e-01 - 1.31067498602735e-01 1.30195755283590e-01 - 1.40354649921884e-01 1.33251824322003e-01 - 1.50055110786138e-01 1.36129604637468e-01 - 1.60148962661562e-01 1.38815571165744e-01 - 1.70658187899640e-01 1.41287745526478e-01 - 1.81574957422924e-01 1.43532606879584e-01 - 1.92907571409635e-01 1.45531916343408e-01 - 2.04657634577812e-01 1.47280205326909e-01 - 2.16817353069425e-01 1.48762723516821e-01 - 2.29396483963478e-01 1.49972342499187e-01 - 2.42377800694080e-01 1.50912768784477e-01 - 2.55773624268338e-01 1.51576424948594e-01 - 2.69566785632899e-01 1.51956788121951e-01 - 2.83765797226135e-01 1.52039300444614e-01 - 2.98347982887804e-01 1.51845427550373e-01 - 3.13318978785268e-01 1.51348560236228e-01 - 3.28658461892810e-01 1.50570737073037e-01 - 3.44364941645546e-01 1.49518753149440e-01 - 3.60419773725681e-01 1.48186753884080e-01 - 3.76811233766957e-01 1.46574117461181e-01 - 3.93525251020729e-01 1.44700405836315e-01 - 4.10538642553571e-01 1.42550209259572e-01 - 4.27843232490823e-01 1.40150965984094e-01 - 4.45406663468198e-01 1.37508289229088e-01 - 4.63222254103030e-01 1.34634823896859e-01 - 4.81251545655716e-01 1.31526295365656e-01 - 4.99481026671737e-01 1.28216290907021e-01 - 5.17879583085697e-01 1.24709999085407e-01 - 5.36417631367010e-01 1.21043272545432e-01 - 5.55075704909560e-01 1.17234409616513e-01 - 5.73808427242608e-01 1.13281393690092e-01 - 5.92596731105059e-01 1.09202082358182e-01 - 6.11401377553511e-01 1.05021414111290e-01 - 6.30186430605241e-01 1.00745789886680e-01 - 6.48926781663159e-01 9.64001060608055e-02 - 6.67570206424973e-01 9.19950451724024e-02 - 6.86088429590952e-01 8.75414075981975e-02 - 7.04445389043917e-01 8.30759814870957e-02 - 7.22592093722966e-01 7.85950561773271e-02 - 7.40501800453524e-01 7.41263265827051e-02 - 7.58125457122835e-01 6.96980524279954e-02 - 7.75421014376153e-01 6.53266343172756e-02 - 7.92362373587600e-01 6.10341558843574e-02 - 8.08894546151696e-01 5.68385830413245e-02 - 8.24974633014891e-01 5.27405326538182e-02 - 8.40576952273409e-01 4.87744704249379e-02 - 8.55652758808818e-01 4.49507709519625e-02 - 8.70162898882712e-01 4.12906024024473e-02 - 8.84085033071272e-01 3.77997753529371e-02 - 8.97361214262371e-01 3.44873884909143e-02 - 9.09954680076662e-01 3.13694271337612e-02 - 9.21851471402547e-01 2.84522709462102e-02 - 9.33012836658427e-01 2.57504864794323e-02 - 9.43389278969050e-01 2.32583523864130e-02 - 9.52973153850560e-01 2.09624268461499e-02 - 9.61743130827061e-01 1.88646105590430e-02 - 9.69640690675464e-01 1.69774472671939e-02 - 9.76664215898664e-01 1.52986757236455e-02 - 9.82815077112014e-01 1.38291681162444e-02 - 9.88028440045103e-01 1.25842495994459e-02 - 9.92304836603751e-01 1.15639944099119e-02 - 9.95693518775914e-01 1.07564013941685e-02 - 9.98120489340015e-01 1.00664339895550e-02 - 9.99443037908705e-01 9.75603172539057e-03 - 1.00000000000000e+00 9.65742580140428e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_21.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_21.dat index ea3ff331..49277ae7 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_21.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_21.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_21_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF21_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF21_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.650470 alpha0 ! 0-lift angle of attack, depends on airfoil. - 14.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -14.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.185916 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.711261 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.023302 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.939797 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.098688 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.010638 Cd0 ! 2D drag coefficient value at 0-lift. - -0.086157 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.012111 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085554 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 8.00522557985044e-03 2.36293053075623e-02 4.90902950034548e-03 --1.77714285740401e+02 6.70148185634155e-02 2.76569572194834e-02 9.15137982337449e-02 --1.75428571400002e+02 1.35209099028400e-01 2.75097282223119e-02 1.82588507104572e-01 --1.73142857116900e+02 1.99341620944980e-01 2.72449534535768e-02 2.74803483415429e-01 --1.70857160423602e+02 2.61033017610808e-01 3.10891593319191e-02 3.65069442606889e-01 --1.68571631778825e+02 3.21900374722339e-01 4.23617754400039e-02 4.01216829381455e-01 --1.66285714267592e+02 3.83579656480780e-01 6.07633873418587e-02 4.02486499526984e-01 --1.63999999984490e+02 4.47676161732485e-01 8.50808401791267e-02 4.02863898666211e-01 --1.61714472886699e+02 5.15810625365283e-01 1.14103734465517e-01 4.05413173373416e-01 --1.59428371284127e+02 5.88610255731747e-01 1.46787967045390e-01 4.10009043681839e-01 --1.57142842639350e+02 6.62572010470661e-01 1.82680195367915e-01 4.26723373482997e-01 --1.54857313994574e+02 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0.00000000000000e+00 2.53290148278653e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_21_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_21_Coords.txt deleted file mode 100644 index 8bed70d6..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_21_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.295080 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -9.10000000000000e-03 - 9.99429683992583e-01 -8.97410087682643e-03 - 9.98063017832965e-01 -8.67598953244562e-03 - 9.95573914266674e-01 -8.14595089213578e-03 - 9.92086309749559e-01 -7.43115994996547e-03 - 9.87686148675057e-01 -6.57536975079162e-03 - 9.82330525170640e-01 -5.60221915947951e-03 - 9.76011908335692e-01 -4.54940973747198e-03 - 9.68787467298381e-01 -3.46997962341700e-03 - 9.60674860259240e-01 -2.41285003089080e-03 - 9.51675358763677e-01 -1.42771987986409e-03 - 9.41827652746244e-01 -5.70050191777702e-04 - 9.31175295355131e-01 4.80801897517226e-05 - 9.19730397431178e-01 4.06860017231694e-04 - 9.07524559194720e-01 4.52269999999998e-04 - 8.94610408070308e-01 1.64419939317424e-04 - 8.81009696499435e-01 -5.70440230176322e-04 - 8.66747905197194e-01 -1.77337046522693e-03 - 8.51890258171205e-01 -3.46747023175701e-03 - 8.36469462621421e-01 -5.67018959149186e-03 - 8.20513485943698e-01 -8.40864074942169e-03 - 8.04073832217581e-01 -1.17002795267195e-02 - 7.87191529885653e-01 -1.55599800277855e-02 - 7.69897919101553e-01 -2.00464702450882e-02 - 7.52252341235159e-01 -2.51232396305170e-02 - 7.34291349178558e-01 -3.07197102645921e-02 - 7.16044924955764e-01 -3.68034182998072e-02 - 6.97571640033109e-01 -4.33309099880336e-02 - 6.78906186433687e-01 -5.02354613409712e-02 - 6.60080312620540e-01 -5.74332189880702e-02 - 6.41147517137212e-01 -6.48181011219733e-02 - 6.22137650968852e-01 -7.23040996187365e-02 - 6.03087998194415e-01 -7.97953107050783e-02 - 5.84045042118975e-01 -8.71799591880897e-02 - 5.65030897687003e-01 -9.43795908613815e-02 - 5.46088602779599e-01 -1.01319709004555e-01 - 5.27248673916899e-01 -1.07918328664370e-01 - 5.08535950506088e-01 -1.14135309837075e-01 - 4.89992355470388e-01 -1.19926011362794e-01 - 4.71632114506831e-01 -1.25255808746972e-01 - 4.53492503744347e-01 -1.30095539048197e-01 - 4.35593302897673e-01 -1.34441039333629e-01 - 4.17956065616942e-01 -1.38294710899550e-01 - 4.00609748442576e-01 -1.41652090279818e-01 - 3.83560931606009e-01 -1.44511309752356e-01 - 3.66843215733716e-01 -1.46898140547306e-01 - 3.50457316320503e-01 -1.48807760375787e-01 - 3.34434484008630e-01 -1.50265289697107e-01 - 3.18774100329315e-01 -1.51278329983845e-01 - 3.03499623121295e-01 -1.51882809938511e-01 - 2.88611293565648e-01 -1.52078610000000e-01 - 2.74124386665666e-01 -1.51898669936677e-01 - 2.60041455523719e-01 -1.51336769777873e-01 - 2.46374872015917e-01 -1.50442920154590e-01 - 2.33123443938834e-01 -1.49217560411589e-01 - 2.20293777810423e-01 -1.47678989710413e-01 - 2.07883282965331e-01 -1.45851750474890e-01 - 1.95902956391646e-01 -1.43751029319193e-01 - 1.84341253066628e-01 -1.41392470667206e-01 - 1.73213930954160e-01 -1.38801290235859e-01 - 1.62499176129638e-01 -1.35981438924875e-01 - 1.52214602777260e-01 -1.32959040856021e-01 - 1.42331759398971e-01 -1.29758709796275e-01 - 1.32872111539190e-01 -1.26397440570926e-01 - 1.23806439629760e-01 -1.22882609850750e-01 - 1.15147623386077e-01 -1.19249911475328e-01 - 1.06887208802748e-01 -1.15508899437748e-01 - 9.90071115215634e-02 -1.11668560766657e-01 - 9.15234043853439e-02 -1.07767882360735e-01 - 8.43970428172224e-02 -1.03803631617791e-01 - 7.76464790199521e-02 -9.98000994015066e-02 - 7.12479082120209e-02 -9.57752288413894e-02 - 6.51878662973747e-02 -9.17284474538027e-02 - 5.94874721274202e-02 -8.76905815487659e-02 - 5.41002464180900e-02 -8.36588972420626e-02 - 4.90378786701877e-02 -7.96477489156003e-02 - 4.43003497573338e-02 -7.56710797905133e-02 - 3.98423597346806e-02 -7.17122897577530e-02 - 3.56899752436130e-02 -6.78137354061000e-02 - 3.18292350050658e-02 -6.39773348947218e-02 - 2.82200072057899e-02 -6.01823369685319e-02 - 2.48925247792699e-02 -5.64570055155849e-02 - 2.18286683030034e-02 -5.28118379107431e-02 - 1.89846947131331e-02 -4.91873962043229e-02 - 1.63921917020335e-02 -4.56621024016769e-02 - 1.40446346341990e-02 -4.22241670532139e-02 - 1.18798249846349e-02 -3.87983781876052e-02 - 9.93094518736223e-03 -3.54753913800425e-02 - 8.21940795734749e-03 -3.22541859724698e-02 - 6.65838622137879e-03 -2.90272017950834e-02 - 5.26774192850643e-03 -2.58536547168384e-02 - 4.09515753852961e-03 -2.27770631817991e-02 - 3.09878859713640e-03 -1.98633557465334e-02 - 2.19660773551101e-03 -1.70269218334997e-02 - 1.46264176301869e-03 -1.39586784828470e-02 - 9.64484608297914e-04 -1.11944720250323e-02 - 5.99373867982851e-04 -7.90892154210597e-03 - 2.90086645599082e-04 -3.84265529311526e-03 - 7.80707788302466e-05 -9.82260086719418e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 9.90415890034858e-04 - 2.89878724192004e-04 3.93425240244667e-03 - 5.98775316682048e-04 8.15934846084688e-03 - 9.63326351634835e-04 1.14844836257862e-02 - 1.45966821282819e-03 1.44022109127572e-02 - 2.19097636449990e-03 1.76260659583381e-02 - 3.08997841959778e-03 2.06917147874302e-02 - 4.08271112470316e-03 2.38586833365981e-02 - 5.24853124383664e-03 2.70792332110040e-02 - 6.63128223001261e-03 3.04174251494330e-02 - 8.18368429859057e-03 3.38470990084275e-02 - 9.88361416849065e-03 3.72302879172865e-02 - 1.18176401547236e-02 4.07364902698880e-02 - 1.39661993216829e-02 4.43429789089220e-02 - 1.62951420791042e-02 4.79351030905318e-02 - 1.88631937781153e-02 5.16146452163195e-02 - 2.16807137532775e-02 5.53639648174378e-02 - 2.47159162958630e-02 5.91230855684436e-02 - 2.80064400105862e-02 6.29268900118276e-02 - 3.15762558914965e-02 6.67825857009716e-02 - 3.53948396168776e-02 7.06546596237477e-02 - 3.94949825480075e-02 7.45554623505188e-02 - 4.38979282781582e-02 7.84946585068906e-02 - 4.85758075737765e-02 8.24276980221222e-02 - 5.35679916138119e-02 8.63747212355996e-02 - 5.88818211488708e-02 9.03159608249575e-02 - 6.45001629027312e-02 9.42234119557792e-02 - 7.04692046391145e-02 9.81210429323970e-02 - 7.67740309924711e-02 1.01980700587738e-01 - 8.34162127168367e-02 1.05787761502348e-01 - 9.04290195190654e-02 1.09531419752205e-01 - 9.77906533229447e-02 1.13194711591968e-01 - 1.05536187198748e-01 1.16770018759087e-01 - 1.13658760041779e-01 1.20226610017070e-01 - 1.22161483318940e-01 1.23565341245443e-01 - 1.31067498602735e-01 1.26763329521138e-01 - 1.40354649921884e-01 1.29805539975700e-01 - 1.50055110786138e-01 1.32676420220292e-01 - 1.60148962661562e-01 1.35360350665810e-01 - 1.70658187899640e-01 1.37840509536677e-01 - 1.81574957422924e-01 1.40099329506392e-01 - 1.92907571409635e-01 1.42118070230667e-01 - 2.04657634577812e-01 1.43894450625358e-01 - 2.16817353069425e-01 1.45407960339178e-01 - 2.29396483963478e-01 1.46656310340653e-01 - 2.42377800694080e-01 1.47639020043373e-01 - 2.55773624268338e-01 1.48350620168271e-01 - 2.69566785632899e-01 1.48782049935750e-01 - 2.83765797226135e-01 1.48918160000000e-01 - 2.98347982887804e-01 1.48782599959359e-01 - 3.13318978785268e-01 1.48345120043633e-01 - 3.28658461892810e-01 1.47628549898609e-01 - 3.44364941645546e-01 1.46641239884898e-01 - 3.60419773725681e-01 1.45374339680188e-01 - 3.76811233766957e-01 1.43830819621408e-01 - 3.93525251020729e-01 1.42028949883109e-01 - 4.10538642553571e-01 1.39950449673306e-01 - 4.27843232490823e-01 1.37626219651329e-01 - 4.45406663468198e-01 1.35058739475010e-01 - 4.63222254103030e-01 1.32262199333811e-01 - 4.81251545655716e-01 1.29230280749919e-01 - 4.99481026671737e-01 1.25997500605207e-01 - 5.17879583085697e-01 1.22564539413305e-01 - 5.36417631367010e-01 1.18971389730730e-01 - 5.55075704909560e-01 1.15235278999886e-01 - 5.73808427242608e-01 1.11351970579916e-01 - 5.92596731105059e-01 1.07342219761247e-01 - 6.11401377553511e-01 1.03228550541675e-01 - 6.30186430605241e-01 9.90183698630362e-02 - 6.48926781663159e-01 9.47360296163077e-02 - 6.67570206424973e-01 9.03933908404354e-02 - 6.86088429590952e-01 8.59995000976221e-02 - 7.04445389043917e-01 8.15928802312875e-02 - 7.22592093722966e-01 7.71688390876221e-02 - 7.40501800453524e-01 7.27567898878689e-02 - 7.58125457122835e-01 6.83836607160974e-02 - 7.75421014376153e-01 6.40659989062092e-02 - 7.92362373587600e-01 5.98264991013292e-02 - 8.08894546151696e-01 5.56812209667287e-02 - 8.24974633014891e-01 5.16342592423786e-02 - 8.40576952273409e-01 4.77193894299814e-02 - 8.55652758808818e-01 4.39421102975473e-02 - 8.70162898882712e-01 4.03284302774180e-02 - 8.84085033071272e-01 3.68818492417327e-02 - 8.97361214262371e-01 3.36128089545598e-02 - 9.09954680076662e-01 3.05357899813582e-02 - 9.21851471402547e-01 2.76563296627401e-02 - 9.33012836658427e-01 2.49894207953904e-02 - 9.43389278969050e-01 2.25287002441622e-02 - 9.52973153850560e-01 2.02618390896561e-02 - 9.61743130827061e-01 1.81893898046564e-02 - 9.69640690675464e-01 1.63249898406273e-02 - 9.76664215898664e-01 1.46686809666731e-02 - 9.82815077112014e-01 1.32196806799961e-02 - 9.88028440045103e-01 1.19927499893902e-02 - 9.92304836603751e-01 1.09872207982655e-02 - 9.95693518775914e-01 1.01910203168246e-02 - 9.98120489340015e-01 9.50000016481772e-03 - 9.99443037908705e-01 9.20000041265724e-03 - 1.00000000000000e+00 9.10000000000000e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_22.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_22.dat index 4f486694..462efd3a 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_22.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_22.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_22_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF22_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF22_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.668559 alpha0 ! 0-lift angle of attack, depends on airfoil. - 14.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -14.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.259467 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.678613 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.028511 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.933694 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.092399 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.010114 Cd0 ! 2D drag coefficient value at 0-lift. - -0.086060 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.011709 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085588 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 5.03385022218753e-03 2.17911233069394e-02 4.90921299165391e-03 --1.77714285740401e+02 6.70673652276191e-02 2.58163409311689e-02 9.15135729199907e-02 --1.75428571400002e+02 1.35266861091860e-01 2.57002154877331e-02 1.82590500112058e-01 --1.73142857116900e+02 1.98396036858345e-01 2.56175494762427e-02 2.74793187887625e-01 --1.70857160423602e+02 2.58605661088405e-01 2.97538240316711e-02 3.65094144538111e-01 --1.68571631778825e+02 3.17900492938906e-01 4.13901889165362e-02 4.00776625270770e-01 --1.66285714267592e+02 3.78218497368829e-01 6.01994270449956e-02 4.01406242682071e-01 --1.63999999984490e+02 4.41493112605930e-01 8.49416256154605e-02 4.01265542952676e-01 --1.61714472886699e+02 5.09685815294068e-01 1.14375932330704e-01 4.02981162809844e-01 --1.59428371284127e+02 5.83568586824531e-01 1.47432449669012e-01 4.07229820926712e-01 --1.57142842639350e+02 6.58894200600734e-01 1.83650568214356e-01 4.23919942618295e-01 --1.54857313994574e+02 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0.00000000000000e+00 2.37292686734004e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_22_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_22_Coords.txt deleted file mode 100644 index e4b8cd47..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_22_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.292851 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -8.49598271988369e-03 - 9.99429683992583e-01 -8.37688850416566e-03 - 9.98063017832965e-01 -8.09462322807536e-03 - 9.95573914266674e-01 -7.59178849722610e-03 - 9.92086309749559e-01 -6.91157385557309e-03 - 9.87686148675057e-01 -6.09412106040932e-03 - 9.82330525170640e-01 -5.16058785003719e-03 - 9.76011908335692e-01 -4.14482655014699e-03 - 9.68787467298381e-01 -3.09492403082238e-03 - 9.60674860259240e-01 -2.05367548447263e-03 - 9.51675358763677e-01 -1.07007269679753e-03 - 9.41827652746244e-01 -2.02461902125930e-04 - 9.31175295355131e-01 4.34976004026813e-04 - 9.19730397431178e-01 8.23160786672592e-04 - 9.07524559194720e-01 9.02733924363157e-04 - 8.94610408070308e-01 6.61684283191464e-04 - 8.81009696499435e-01 -1.81841156007604e-05 - 8.66747905197194e-01 -1.15524494209969e-03 - 8.51890258171205e-01 -2.77019201762577e-03 - 8.36469462621421e-01 -4.88092229376838e-03 - 8.20513485943698e-01 -7.51789954674598e-03 - 8.04073832217581e-01 -1.07007014602159e-02 - 7.87191529885653e-01 -1.44505469526872e-02 - 7.69897919101553e-01 -1.88272032949802e-02 - 7.52252341235159e-01 -2.37957780860946e-02 - 7.34291349178558e-01 -2.92838745014934e-02 - 7.16044924955764e-01 -3.52611393554542e-02 - 6.97571640033109e-01 -4.16846126834599e-02 - 6.78906186433687e-01 -4.84880917538675e-02 - 6.60080312620540e-01 -5.55923534820457e-02 - 6.41147517137212e-01 -6.28915093743065e-02 - 6.22137650968852e-01 -7.02989621340141e-02 - 6.03087998194415e-01 -7.77165316191965e-02 - 5.84045042118975e-01 -8.50316088948650e-02 - 5.65030897687003e-01 -9.21653424673844e-02 - 5.46088602779599e-01 -9.90416697646080e-02 - 5.27248673916899e-01 -1.05579414058498e-01 - 5.08535950506088e-01 -1.11737719847175e-01 - 4.89992355470388e-01 -1.17467483814353e-01 - 4.71632114506831e-01 -1.22735147123803e-01 - 4.53492503744347e-01 -1.27514058717594e-01 - 4.35593302897673e-01 -1.31799893076352e-01 - 4.17956065616942e-01 -1.35596083453546e-01 - 4.00609748442576e-01 -1.38901633791227e-01 - 3.83560931606009e-01 -1.41709466443930e-01 - 3.66843215733716e-01 -1.44048464010112e-01 - 3.50457316320503e-01 -1.45912012962401e-01 - 3.34434484008630e-01 -1.47325893099887e-01 - 3.18774100329315e-01 -1.48298826900033e-01 - 3.03499623121295e-01 -1.48864641322088e-01 - 2.88611293565648e-01 -1.49024941996817e-01 - 2.74124386665666e-01 -1.48813768343706e-01 - 2.60041455523719e-01 -1.48223166719853e-01 - 2.46374872015917e-01 -1.47303909755262e-01 - 2.33123443938834e-01 -1.46056768984463e-01 - 2.20293777810423e-01 -1.44497967662118e-01 - 2.07883282965331e-01 -1.42655170564801e-01 - 1.95902956391646e-01 -1.40540104733994e-01 - 1.84341253066628e-01 -1.38169172577813e-01 - 1.73213930954160e-01 -1.35567014245769e-01 - 1.62499176129638e-01 -1.32738971876582e-01 - 1.52214602777260e-01 -1.29713456327452e-01 - 1.42331759398971e-01 -1.26513229949788e-01 - 1.32872111539190e-01 -1.23155031555425e-01 - 1.23806439629760e-01 -1.19648839499171e-01 - 1.15147623386077e-01 -1.16026743211752e-01 - 1.06887208802748e-01 -1.12301901649207e-01 - 9.90071115215634e-02 -1.08482807312057e-01 - 9.15234043853439e-02 -1.04610775032477e-01 - 8.43970428172224e-02 -1.00678790301502e-01 - 7.76464790199521e-02 -9.67153980717850e-02 - 7.12479082120209e-02 -9.27339067760254e-02 - 6.51878662973747e-02 -8.87371121303093e-02 - 5.94874721274202e-02 -8.47535062750939e-02 - 5.41002464180900e-02 -8.07796258572112e-02 - 4.90378786701877e-02 -7.68340385617690e-02 - 4.43003497573338e-02 -7.29379649633312e-02 - 3.98423597346806e-02 -6.90670099865746e-02 - 3.56899752436130e-02 -6.52610136623509e-02 - 3.18292350050658e-02 -6.15217522364905e-02 - 2.82200072057899e-02 -5.78280909785851e-02 - 2.48925247792699e-02 -5.42092079452242e-02 - 2.18286683030034e-02 -5.06719367949185e-02 - 1.89846947131331e-02 -4.71594103337036e-02 - 1.63921917020335e-02 -4.37480823288584e-02 - 1.40446346341990e-02 -4.04311081335092e-02 - 1.18798249846349e-02 -3.71239207897985e-02 - 9.93094518736223e-03 -3.39134394554640e-02 - 8.21940795734749e-03 -3.08091792695308e-02 - 6.65838622137879e-03 -2.77094695236257e-02 - 5.26774192850643e-03 -2.46746650287744e-02 - 4.09515753852961e-03 -2.17386283176186e-02 - 3.09878859713640e-03 -1.89857519011694e-02 - 2.19660773551101e-03 -1.63932321566283e-02 - 1.46264176301869e-03 -1.35491020384277e-02 - 9.64484608297914e-04 -1.08791883824086e-02 - 5.99373867982851e-04 -7.62331073660606e-03 - 2.90086645599082e-04 -3.68384509129018e-03 - 7.80707788302466e-05 -9.44663307140894e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 9.80411782838919e-04 - 2.89878724192004e-04 3.95653579414230e-03 - 5.98775316682048e-04 8.11613389355538e-03 - 9.63326351634835e-04 1.12721928207648e-02 - 1.45966821282819e-03 1.41029736248487e-02 - 2.19097636449990e-03 1.71764420126930e-02 - 3.08997841959778e-03 2.01459278285974e-02 - 4.08271112470316e-03 2.31944440181847e-02 - 5.24853124383664e-03 2.62922394157900e-02 - 6.63128223001261e-03 2.95191241847042e-02 - 8.18368429859057e-03 3.28210601461603e-02 - 9.88361416849065e-03 3.60954037091099e-02 - 1.18176401547236e-02 3.94965909932381e-02 - 1.39661993216829e-02 4.29940794701408e-02 - 1.62951420791042e-02 4.64831324171463e-02 - 1.88631937781153e-02 5.00552279602206e-02 - 2.16807137532775e-02 5.36949797042503e-02 - 2.47159162958630e-02 5.73445358646541e-02 - 2.80064400105862e-02 6.10343017550221e-02 - 3.15762558914965e-02 6.47966007068220e-02 - 3.53948396168776e-02 6.85980131390710e-02 - 3.94949825480075e-02 7.24302500559372e-02 - 4.38979282781582e-02 7.62979504764624e-02 - 4.85758075737765e-02 8.01545771070289e-02 - 5.35679916138119e-02 8.40271208092890e-02 - 5.88818211488708e-02 8.78944096613417e-02 - 6.45001629027312e-02 9.17304945984814e-02 - 7.04692046391145e-02 9.55594655082250e-02 - 7.67740309924711e-02 9.93522650696601e-02 - 8.34162127168367e-02 1.03097970954478e-01 - 9.04290195190654e-02 1.06782931422455e-01 - 9.77906533229447e-02 1.10394066632836e-01 - 1.05536187198748e-01 1.13920354903335e-01 - 1.13658760041779e-01 1.17334572793877e-01 - 1.22161483318940e-01 1.20637071369476e-01 - 1.31067498602735e-01 1.23804514541074e-01 - 1.40354649921884e-01 1.26820625315868e-01 - 1.50055110786138e-01 1.29673662988124e-01 - 1.60148962661562e-01 1.32342312247132e-01 - 1.70658187899640e-01 1.34814620273931e-01 - 1.81574957422924e-01 1.37072740295626e-01 - 1.92907571409635e-01 1.39097939849510e-01 - 2.04657634577812e-01 1.40885361087577e-01 - 2.16817353069425e-01 1.42414865737489e-01 - 2.29396483963478e-01 1.43685993936641e-01 - 2.42377800694080e-01 1.44697362500282e-01 - 2.55773624268338e-01 1.45441352340690e-01 - 2.69566785632899e-01 1.45907954455813e-01 - 2.83765797226135e-01 1.46085454147881e-01 - 2.98347982887804e-01 1.45991257045592e-01 - 3.13318978785268e-01 1.45599207926958e-01 - 3.28658461892810e-01 1.44932056330546e-01 - 3.44364941645546e-01 1.43993705840905e-01 - 3.60419773725681e-01 1.42776224408819e-01 - 3.76811233766957e-01 1.41286384970234e-01 - 3.93525251020729e-01 1.39538933301757e-01 - 4.10538642553571e-01 1.37518208844612e-01 - 4.27843232490823e-01 1.35251911065497e-01 - 4.45406663468198e-01 1.32742962835800e-01 - 4.63222254103030e-01 1.30006823286330e-01 - 4.81251545655716e-01 1.27035593131461e-01 - 4.99481026671737e-01 1.23864521629489e-01 - 5.17879583085697e-01 1.20492574406992e-01 - 5.36417631367010e-01 1.16960521373873e-01 - 5.55075704909560e-01 1.13282338108597e-01 - 5.73808427242608e-01 1.09457201428486e-01 - 5.92596731105059e-01 1.05506758404026e-01 - 6.11401377553511e-01 1.01449265452517e-01 - 6.30186430605241e-01 9.72953260531140e-02 - 6.48926781663159e-01 9.30677039213725e-02 - 6.67570206424973e-01 8.87805389866934e-02 - 6.86088429590952e-01 8.44434106412547e-02 - 7.04445389043917e-01 8.00911797050433e-02 - 7.22592093722966e-01 7.57232261045524e-02 - 7.40501800453524e-01 7.13686541060618e-02 - 7.58125457122835e-01 6.70521774259920e-02 - 7.75421014376153e-01 6.27904733172418e-02 - 7.92362373587600e-01 5.86072052830065e-02 - 8.08894546151696e-01 5.45161347312083e-02 - 8.24974633014891e-01 5.05248661115650e-02 - 8.40576952273409e-01 4.66658787019443e-02 - 8.55652758808818e-01 4.29408740945420e-02 - 8.70162898882712e-01 3.93779779436818e-02 - 8.84085033071272e-01 3.59811336093471e-02 - 8.97361214262371e-01 3.27594776743387e-02 - 9.09954680076662e-01 2.97281369203677e-02 - 9.21851471402547e-01 2.68892078776931e-02 - 9.33012836658427e-01 2.42608197214284e-02 - 9.43389278969050e-01 2.18356996207559e-02 - 9.52973153850560e-01 1.96034075171455e-02 - 9.61743130827061e-01 1.75621306957766e-02 - 9.69640690675464e-01 1.57244498914358e-02 - 9.76664215898664e-01 1.40926258469457e-02 - 9.82815077112014e-01 1.26655583849478e-02 - 9.88028440045103e-01 1.14562687552045e-02 - 9.92304836603751e-01 1.04649419111254e-02 - 9.95693518775914e-01 9.68011433017247e-03 - 9.98120489340015e-01 9.01130178949829e-03 - 9.99443037908705e-01 8.71447508534717e-03 - 1.00000000000000e+00 8.61270243891381e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_23.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_23.dat index 7a79c4a4..8798949f 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_23.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_23.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_23_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF23_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF23_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.715671 alpha0 ! 0-lift angle of attack, depends on airfoil. - 14.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -14.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.323019 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.625684 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.033371 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.914723 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.083708 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.009457 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085840 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.011299 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085673 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -2.65907796243741e-03 1.96660846781985e-02 4.90931729854681e-03 --1.77714285740401e+02 6.72034092023451e-02 2.36749841379878e-02 9.15129895798464e-02 --1.75428571400002e+02 1.35416407800877e-01 2.36001409042081e-02 1.82595660033514e-01 --1.73142857116900e+02 1.97710452837031e-01 2.37122924978138e-02 2.74766532636612e-01 --1.70857160423602e+02 2.56453950953318e-01 2.81591949577664e-02 3.65158098148824e-01 --1.68571631778825e+02 3.13988035910119e-01 4.01967309834360e-02 4.00330148829235e-01 --1.66285714267592e+02 3.72757330531973e-01 5.94794152000968e-02 4.00309654468218e-01 --1.63999999984490e+02 4.35207111334431e-01 8.47468004497875e-02 3.99744932337435e-01 --1.61714472886699e+02 5.03751043657953e-01 1.14736923778262e-01 4.00544628882791e-01 --1.59428371284127e+02 5.79181148759764e-01 1.48359850735087e-01 4.04512558070226e-01 --1.57142842639350e+02 6.56092777420682e-01 1.85152677714045e-01 4.21220113338481e-01 --1.54857313994574e+02 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0.00000000000000e+00 2.17374823223351e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_23_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_23_Coords.txt deleted file mode 100644 index e016c416..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_23_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.290988 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -7.85074908408851e-03 - 9.99429683992583e-01 -7.73902530962847e-03 - 9.98063017832965e-01 -7.47365118288840e-03 - 9.95573914266674e-01 -6.99883622928392e-03 - 9.92086309749559e-01 -6.35206892841020e-03 - 9.87686148675057e-01 -5.56649902635840e-03 - 9.82330525170640e-01 -4.66166382129300e-03 - 9.76011908335692e-01 -3.67019099652444e-03 - 9.68787467298381e-01 -2.63816160112357e-03 - 9.60674860259240e-01 -1.60614017008510e-03 - 9.51675358763677e-01 -6.25811612833402e-04 - 9.41827652746244e-01 2.45342435322138e-04 - 9.31175295355131e-01 9.08207189434444e-04 - 9.19730397431178e-01 1.33744838860717e-03 - 9.07524559194720e-01 1.46479976406745e-03 - 8.94610408070308e-01 1.28153816155727e-03 - 8.81009696499435e-01 6.71669052397427e-04 - 8.66747905197194e-01 -3.83252370445055e-04 - 8.51890258171205e-01 -1.90166312758675e-03 - 8.36469462621421e-01 -3.90529776831212e-03 - 8.20513485943698e-01 -6.42227824655784e-03 - 8.04073832217581e-01 -9.47887880980430e-03 - 7.87191529885653e-01 -1.31031327817203e-02 - 7.69897919101553e-01 -1.73537977288908e-02 - 7.52252341235159e-01 -2.21997505481735e-02 - 7.34291349178558e-01 -2.75700113695905e-02 - 7.16044924955764e-01 -3.34332764850428e-02 - 6.97571640033109e-01 -3.97437145565732e-02 - 6.78906186433687e-01 -4.64387235113726e-02 - 6.60080312620540e-01 -5.34408525829114e-02 - 6.41147517137212e-01 -6.06473294676908e-02 - 6.22137650968852e-01 -6.79685686396122e-02 - 6.03087998194415e-01 -7.53032659189456e-02 - 5.84045042118975e-01 -8.25442516754123e-02 - 5.65030897687003e-01 -8.96056442574128e-02 - 5.46088602779599e-01 -9.64116694750528e-02 - 5.27248673916899e-01 -1.02883670756215e-01 - 5.08535950506088e-01 -1.08979711473384e-01 - 4.89992355470388e-01 -1.14643938733714e-01 - 4.71632114506831e-01 -1.19845953074039e-01 - 4.53492503744347e-01 -1.24562592038118e-01 - 4.35593302897673e-01 -1.28786770492839e-01 - 4.17956065616942e-01 -1.32520968118955e-01 - 4.00609748442576e-01 -1.35771324274698e-01 - 3.83560931606009e-01 -1.38524285425359e-01 - 3.66843215733716e-01 -1.40810491373660e-01 - 3.50457316320503e-01 -1.42624229671433e-01 - 3.34434484008630e-01 -1.43991673092873e-01 - 3.18774100329315e-01 -1.44923945591859e-01 - 3.03499623121295e-01 -1.45448123900445e-01 - 2.88611293565648e-01 -1.45573497980716e-01 - 2.74124386665666e-01 -1.45330536416332e-01 - 2.60041455523719e-01 -1.44714135612348e-01 - 2.46374872015917e-01 -1.43770461015772e-01 - 2.33123443938834e-01 -1.42505656110575e-01 - 2.20293777810423e-01 -1.40931013824344e-01 - 2.07883282965331e-01 -1.39078660628970e-01 - 1.95902956391646e-01 -1.36956715820140e-01 - 1.84341253066628e-01 -1.34581530194154e-01 - 1.73213930954160e-01 -1.31977749612643e-01 - 1.62499176129638e-01 -1.29153479043250e-01 - 1.52214602777260e-01 -1.26138450297913e-01 - 1.42331759398971e-01 -1.22952339820219e-01 - 1.32872111539190e-01 -1.19610862093457e-01 - 1.23806439629760e-01 -1.16129272176430e-01 - 1.15147623386077e-01 -1.12532916836769e-01 - 1.06887208802748e-01 -1.08839558300592e-01 - 9.90071115215634e-02 -1.05057830377014e-01 - 9.15234043853439e-02 -1.01230232687796e-01 - 8.43970428172224e-02 -9.73434030354098e-02 - 7.76464790199521e-02 -9.34331156414663e-02 - 7.12479082120209e-02 -8.95040787723833e-02 - 6.51878662973747e-02 -8.55651166575001e-02 - 5.94874721274202e-02 -8.16414347810076e-02 - 5.41002464180900e-02 -7.77287367808805e-02 - 4.90378786701877e-02 -7.38532738148395e-02 - 4.43003497573338e-02 -7.00477941219068e-02 - 3.98423597346806e-02 -6.62741656953677e-02 - 3.56899752436130e-02 -6.25687072743394e-02 - 3.18292350050658e-02 -5.89328695171523e-02 - 2.82200072057899e-02 -5.53434986750083e-02 - 2.48925247792699e-02 -5.18331539999961e-02 - 2.18286683030034e-02 -4.84027846311145e-02 - 1.89846947131331e-02 -4.50026439991411e-02 - 1.63921917020335e-02 -4.17052775667137e-02 - 1.40446346341990e-02 -3.85164997499487e-02 - 1.18798249846349e-02 -3.53314561542986e-02 - 9.93094518736223e-03 -3.22313345265927e-02 - 8.21940795734749e-03 -2.92421088081934e-02 - 6.65838622137879e-03 -2.62652332716439e-02 - 5.26774192850643e-03 -2.33559811844184e-02 - 4.09515753852961e-03 -2.05493317490119e-02 - 3.09878859713640e-03 -1.79356180143040e-02 - 2.19660773551101e-03 -1.55327841328063e-02 - 1.46264176301869e-03 -1.28961217566295e-02 - 9.64484608297914e-04 -1.03931763172381e-02 - 5.99373867982851e-04 -7.30803751671467e-03 - 2.90086645599082e-04 -3.54995516718107e-03 - 7.80707788302466e-05 -9.09833835173017e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 9.81181326270801e-04 - 2.89878724192004e-04 3.98853508663403e-03 - 5.98775316682048e-04 8.10418216317680e-03 - 9.63326351634835e-04 1.10822295674254e-02 - 1.45966821282819e-03 1.37923967078118e-02 - 2.19097636449990e-03 1.67119633609640e-02 - 3.08997841959778e-03 1.96337535013240e-02 - 4.08271112470316e-03 2.25831016258660e-02 - 5.24853124383664e-03 2.55745048382327e-02 - 6.63128223001261e-03 2.87029551566555e-02 - 8.18368429859057e-03 3.18787905748865e-02 - 9.88361416849065e-03 3.50466701104446e-02 - 1.18176401547236e-02 3.83427707300782e-02 - 1.39661993216829e-02 4.17295906298323e-02 - 1.62951420791042e-02 4.51156609873526e-02 - 1.88631937781153e-02 4.85789139453121e-02 - 2.16807137532775e-02 5.21073091788650e-02 - 2.47159162958630e-02 5.56450259144535e-02 - 2.80064400105862e-02 5.92166248769848e-02 - 3.15762558914965e-02 6.28891794254173e-02 - 3.53948396168776e-02 6.66306336489364e-02 - 3.94949825480075e-02 7.04043970608463e-02 - 4.38979282781582e-02 7.42084183374873e-02 - 4.85758075737765e-02 7.79930382111677e-02 - 5.35679916138119e-02 8.17941001196384e-02 - 5.88818211488708e-02 8.55897550617805e-02 - 6.45001629027312e-02 8.93554434915076e-02 - 7.04692046391145e-02 9.31154130838583e-02 - 7.67740309924711e-02 9.68392193898821e-02 - 8.34162127168367e-02 1.00520728927863e-01 - 9.04290195190654e-02 1.04142622420436e-01 - 9.77906533229447e-02 1.07697175490290e-01 - 1.05536187198748e-01 1.11168697672685e-01 - 1.13658760041779e-01 1.14535229842779e-01 - 1.22161483318940e-01 1.17794977594119e-01 - 1.31067498602735e-01 1.20925318799123e-01 - 1.40354649921884e-01 1.23908283175378e-01 - 1.50055110786138e-01 1.26737738599724e-01 - 1.60148962661562e-01 1.29383845034736e-01 - 1.70658187899640e-01 1.31840453577701e-01 - 1.81574957422924e-01 1.34091072240299e-01 - 1.92907571409635e-01 1.36117221343779e-01 - 2.04657634577812e-01 1.37908448872427e-01 - 2.16817353069425e-01 1.39447743001811e-01 - 2.29396483963478e-01 1.40735710442753e-01 - 2.42377800694080e-01 1.41771424982803e-01 - 2.55773624268338e-01 1.42542837507826e-01 - 2.69566785632899e-01 1.43039368014943e-01 - 2.83765797226135e-01 1.43255858744554e-01 - 2.98347982887804e-01 1.43197959824987e-01 - 3.13318978785268e-01 1.42848191962104e-01 - 3.28658461892810e-01 1.42228991818811e-01 - 3.44364941645546e-01 1.41335665569795e-01 - 3.60419773725681e-01 1.40163593744260e-01 - 3.76811233766957e-01 1.38724075012888e-01 - 3.93525251020729e-01 1.37026539608242e-01 - 4.10538642553571e-01 1.35060989638852e-01 - 4.27843232490823e-01 1.32848202273607e-01 - 4.45406663468198e-01 1.30393313299203e-01 - 4.63222254103030e-01 1.27713273615473e-01 - 4.81251545655716e-01 1.24798415917281e-01 - 4.99481026671737e-01 1.21685014617862e-01 - 5.17879583085697e-01 1.18371296678036e-01 - 5.36417631367010e-01 1.14897290799267e-01 - 5.55075704909560e-01 1.11271844884925e-01 - 5.73808427242608e-01 1.07501464849401e-01 - 5.92596731105059e-01 1.03607857206683e-01 - 6.11401377553511e-01 9.96030368637009e-02 - 6.30186430605241e-01 9.55028006231399e-02 - 6.48926781663159e-01 9.13272936038383e-02 - 6.67570206424973e-01 8.70943557937444e-02 - 6.86088429590952e-01 8.28154223873356e-02 - 7.04445389043917e-01 7.85175587258284e-02 - 7.22592093722966e-01 7.42084802903019e-02 - 7.40501800453524e-01 6.99154515394833e-02 - 7.58125457122835e-01 6.56600193950426e-02 - 7.75421014376153e-01 6.14589172324534e-02 - 7.92362373587600e-01 5.73371836086809e-02 - 8.08894546151696e-01 5.33055747303457e-02 - 8.24974633014891e-01 4.93760198708657e-02 - 8.40576952273409e-01 4.55790675081642e-02 - 8.55652758808818e-01 4.19123267221139e-02 - 8.70162898882712e-01 3.84051266237229e-02 - 8.84085033071272e-01 3.50633328751242e-02 - 8.97361214262371e-01 3.18931309900068e-02 - 9.09954680076662e-01 2.89117971021067e-02 - 9.21851471402547e-01 2.61158877399864e-02 - 9.33012836658427e-01 2.35287710543048e-02 - 9.43389278969050e-01 2.11416559613143e-02 - 9.52973153850560e-01 1.89466263274681e-02 - 9.61743130827061e-01 1.69387887262359e-02 - 9.69640690675464e-01 1.51286056529215e-02 - 9.76664215898664e-01 1.35212106801763e-02 - 9.82815077112014e-01 1.21157231426247e-02 - 9.88028440045103e-01 1.09226774223907e-02 - 9.92304836603751e-01 9.94403746447171e-03 - 9.95693518775914e-01 9.16940486526106e-03 - 9.98120489340015e-01 8.53465790422745e-03 - 9.99443037908705e-01 8.23948702169956e-03 - 1.00000000000000e+00 8.13258762368616e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_24.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_24.dat index 6989515e..6d8c7b15 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_24.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_24.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_24_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF24_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF24_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.775182 alpha0 ! 0-lift angle of attack, depends on airfoil. - 14.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -14.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.389308 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.567476 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.037321 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.893044 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.075639 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.008763 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085605 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.010886 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085802 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -1.22349246252176e-02 1.75437012249047e-02 4.90938893697743e-03 --1.77714285740401e+02 6.73727512539159e-02 2.15186952968214e-02 9.15122634615674e-02 --1.75428571400002e+02 1.35602557511378e-01 2.14829703147913e-02 1.82602082895585e-01 --1.73142857116900e+02 1.97121542182853e-01 2.17607139185703e-02 2.74733353255453e-01 --1.70857160423602e+02 2.54422531691566e-01 2.64874775071059e-02 3.65237705023479e-01 --1.68571631778825e+02 3.10174340088764e-01 3.89157588498505e-02 3.99873589702734e-01 --1.66285714267592e+02 3.67374412445845e-01 5.86877127876183e-02 3.99180439577688e-01 --1.63999999984490e+02 4.29012101971248e-01 8.45248564110444e-02 3.98210846701065e-01 --1.61714472886699e+02 4.97975579763421e-01 1.15148692911909e-01 3.98051973397814e-01 --1.59428371284127e+02 5.75060517777984e-01 1.49453313455402e-01 4.01750360938229e-01 --1.57142842639350e+02 6.53614688798828e-01 1.86975503375231e-01 4.18505328021430e-01 --1.54857313994574e+02 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0.00000000000000e+00 1.95526618668160e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_24_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_24_Coords.txt deleted file mode 100644 index 911c4fb6..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_24_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.289446 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -7.19132636588104e-03 - 9.99429683992583e-01 -7.08679983834179e-03 - 9.98063017832965e-01 -6.83780497491680e-03 - 9.95573914266674e-01 -6.38973041572447e-03 - 9.92086309749559e-01 -5.77385876259451e-03 - 9.87686148675057e-01 -5.01490527200220e-03 - 9.82330525170640e-01 -4.13133078843471e-03 - 9.76011908335692e-01 -3.15608936478425e-03 - 9.68787467298381e-01 -2.13505474559233e-03 - 9.60674860259240e-01 -1.10897916687906e-03 - 9.51675358763677e-01 -1.33620876612322e-04 - 9.41827652746244e-01 7.37124789499028e-04 - 9.31175295355131e-01 1.42811606746666e-03 - 9.19730397431178e-01 1.90380923495650e-03 - 9.07524559194720e-01 2.08594426422786e-03 - 8.94610408070308e-01 1.96496202141228e-03 - 8.81009696499435e-01 1.43242334255196e-03 - 8.66747905197194e-01 4.67512742515619e-04 - 8.51890258171205e-01 -9.45843142609576e-04 - 8.36469462621421e-01 -2.83513703829474e-03 - 8.20513485943698e-01 -5.22297350598879e-03 - 8.04073832217581e-01 -8.14429411182140e-03 - 7.87191529885653e-01 -1.16339562122974e-02 - 7.69897919101553e-01 -1.57483150003549e-02 - 7.52252341235159e-01 -2.04612499011250e-02 - 7.34291349178558e-01 -2.57058375014560e-02 - 7.16044924955764e-01 -3.14477593185340e-02 - 6.97571640033109e-01 -3.76366828627806e-02 - 6.78906186433687e-01 -4.42154551226038e-02 - 6.60080312620540e-01 -5.11065742799301e-02 - 6.41147517137212e-01 -5.82121212414745e-02 - 6.22137650968852e-01 -6.54383659650163e-02 - 6.03087998194415e-01 -7.26807129269736e-02 - 5.84045042118975e-01 -7.98410485067447e-02 - 5.65030897687003e-01 -8.68230027760096e-02 - 5.46088602779599e-01 -9.35521409238378e-02 - 5.27248673916899e-01 -9.99532405804118e-02 - 5.08535950506088e-01 -1.05982860000123e-01 - 4.89992355470388e-01 -1.11577907435216e-01 - 4.71632114506831e-01 -1.16711708315325e-01 - 4.53492503744347e-01 -1.21364724782163e-01 - 4.35593302897673e-01 -1.25525669214057e-01 - 4.17956065616942e-01 -1.29195139042979e-01 - 4.00609748442576e-01 -1.32387644123933e-01 - 3.83560931606009e-01 -1.35083683046622e-01 - 3.66843215733716e-01 -1.37314086314860e-01 - 3.50457316320503e-01 -1.39075963729065e-01 - 3.34434484008630e-01 -1.40395626682559e-01 - 3.18774100329315e-01 -1.41287354348988e-01 - 3.03499623121295e-01 -1.41768954822613e-01 - 2.88611293565648e-01 -1.41860825121622e-01 - 2.74124386665666e-01 -1.41586719867110e-01 - 2.60041455523719e-01 -1.40947769868762e-01 - 2.46374872015917e-01 -1.39982068156547e-01 - 2.33123443938834e-01 -1.38704035821998e-01 - 2.20293777810423e-01 -1.37118846061180e-01 - 2.07883282965331e-01 -1.35263067917799e-01 - 1.95902956391646e-01 -1.33141919370899e-01 - 1.84341253066628e-01 -1.30770932281868e-01 - 1.73213930954160e-01 -1.28175360377966e-01 - 1.62499176129638e-01 -1.25366494157526e-01 - 1.52214602777260e-01 -1.22374619614334e-01 - 1.42331759398971e-01 -1.19215799559127e-01 - 1.32872111539190e-01 -1.15904594351950e-01 - 1.23806439629760e-01 -1.12462387402951e-01 - 1.15147623386077e-01 -1.08906536106086e-01 - 1.06887208802748e-01 -1.05259576922338e-01 - 9.90071115215634e-02 -1.01530528075869e-01 - 9.15234043853439e-02 -9.77621017488089e-02 - 8.43970428172224e-02 -9.39339947863173e-02 - 7.76464790199521e-02 -9.00897965952213e-02 - 7.12479082120209e-02 -8.62244212333988e-02 - 6.51878662973747e-02 -8.23535109614314e-02 - 5.94874721274202e-02 -7.84986868063689e-02 - 5.41002464180900e-02 -7.46549571193466e-02 - 4.90378786701877e-02 -7.08572935318190e-02 - 4.43003497573338e-02 -6.71505470342697e-02 - 3.98423597346806e-02 -6.34813599400860e-02 - 3.56899752436130e-02 -5.98821198838774e-02 - 3.18292350050658e-02 -5.63539687329108e-02 - 2.82200072057899e-02 -5.28709015703322e-02 - 2.48925247792699e-02 -4.94701175666724e-02 - 2.18286683030034e-02 -4.61458551564509e-02 - 1.89846947131331e-02 -4.28580396718892e-02 - 1.63921917020335e-02 -3.96739568397382e-02 - 1.40446346341990e-02 -3.66139815455544e-02 - 1.18798249846349e-02 -3.35506352635565e-02 - 9.93094518736223e-03 -3.05586010571487e-02 - 8.21940795734749e-03 -2.76810349821721e-02 - 6.65838622137879e-03 -2.48207065254698e-02 - 5.26774192850643e-03 -2.20293805688951e-02 - 4.09515753852961e-03 -1.93455801261220e-02 - 3.09878859713640e-03 -1.68507264473933e-02 - 2.19660773551101e-03 -1.45797036637725e-02 - 1.46264176301869e-03 -1.21124530597469e-02 - 9.64484608297914e-04 -9.79906297518846e-03 - 5.99373867982851e-04 -6.96756954902574e-03 - 2.90086645599082e-04 -3.43132197460798e-03 - 7.80707788302466e-05 -8.81665173596313e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 9.82038634333776e-04 - 2.89878724192004e-04 4.01568282282811e-03 - 5.98775316682048e-04 8.09470704686610e-03 - 9.63326351634835e-04 1.08849085850448e-02 - 1.45966821282819e-03 1.34656934870560e-02 - 2.19097636449990e-03 1.62454020200468e-02 - 3.08997841959778e-03 1.91513879149108e-02 - 4.08271112470316e-03 2.20167726999746e-02 - 5.24853124383664e-03 2.49171337770326e-02 - 6.63128223001261e-03 2.79605708948751e-02 - 8.18368429859057e-03 3.10189124416073e-02 - 9.88361416849065e-03 3.40862720700683e-02 - 1.18176401547236e-02 3.72825816149126e-02 - 1.39661993216829e-02 4.05631776373221e-02 - 1.62951420791042e-02 4.38508074355760e-02 - 1.88631937781153e-02 4.72100677876775e-02 - 2.16807137532775e-02 5.06319987397954e-02 - 2.47159162958630e-02 5.40626931163647e-02 - 2.80064400105862e-02 5.75207346483018e-02 - 3.15762558914965e-02 6.11078763251513e-02 - 3.53948396168776e-02 6.47932235868626e-02 - 3.94949825480075e-02 6.85119769814416e-02 - 4.38979282781582e-02 7.22554310065857e-02 - 4.85758075737765e-02 7.59706897737337e-02 - 5.35679916138119e-02 7.97020818063372e-02 - 5.88818211488708e-02 8.34278952929852e-02 - 6.45001629027312e-02 8.71245350338459e-02 - 7.04692046391145e-02 9.08161020036048e-02 - 7.67740309924711e-02 9.44707833535686e-02 - 8.34162127168367e-02 9.80871888396244e-02 - 9.04290195190654e-02 1.01644664265894e-01 - 9.77906533229447e-02 1.05140748318133e-01 - 1.05536187198748e-01 1.08555157576100e-01 - 1.13658760041779e-01 1.11871664825168e-01 - 1.22161483318940e-01 1.15085498646280e-01 - 1.31067498602735e-01 1.18175622429740e-01 - 1.40354649921884e-01 1.21122193298182e-01 - 1.50055110786138e-01 1.23924952546052e-01 - 1.60148962661562e-01 1.26545202073338e-01 - 1.70658187899640e-01 1.28982415806561e-01 - 1.81574957422924e-01 1.31222166139594e-01 - 1.92907571409635e-01 1.33246396571529e-01 - 2.04657634577812e-01 1.35037861951947e-01 - 2.16817353069425e-01 1.36584027475039e-01 - 2.29396483963478e-01 1.37885871306718e-01 - 2.42377800694080e-01 1.38943354428213e-01 - 2.55773624268338e-01 1.39739222975289e-01 - 2.69566785632899e-01 1.40262723026851e-01 - 2.83765797226135e-01 1.40515793957798e-01 - 2.98347982887804e-01 1.40490644867472e-01 - 3.13318978785268e-01 1.40180212101076e-01 - 3.28658461892810e-01 1.39605797553014e-01 - 3.44364941645546e-01 1.38753302749215e-01 - 3.60419773725681e-01 1.37622218223514e-01 - 3.76811233766957e-01 1.36228313886302e-01 - 3.93525251020729e-01 1.34575147120466e-01 - 4.10538642553571e-01 1.32660011886221e-01 - 4.27843232490823e-01 1.30494981948220e-01 - 4.45406663468198e-01 1.28088292923323e-01 - 4.63222254103030e-01 1.25458270650472e-01 - 4.81251545655716e-01 1.22593989997278e-01 - 4.99481026671737e-01 1.19532135431518e-01 - 5.17879583085697e-01 1.16271592111691e-01 - 5.36417631367010e-01 1.12850231317831e-01 - 5.55075704909560e-01 1.09271434787660e-01 - 5.73808427242608e-01 1.05550524696750e-01 - 5.92596731105059e-01 1.01708700066996e-01 - 6.11401377553511e-01 9.77514914345030e-02 - 6.30186430605241e-01 9.37002823726303e-02 - 6.48926781663159e-01 8.95726271313379e-02 - 6.67570206424973e-01 8.53903606013606e-02 - 6.86088429590952e-01 8.11676721351802e-02 - 7.04445389043917e-01 7.69221308489476e-02 - 7.22592093722966e-01 7.26714479969871e-02 - 7.40501800453524e-01 6.84400990825064e-02 - 7.58125457122835e-01 6.42465841336044e-02 - 7.75421014376153e-01 6.01074677386162e-02 - 7.92362373587600e-01 5.60490526899776e-02 - 8.08894546151696e-01 5.20790898244187e-02 - 8.24974633014891e-01 4.82139800328129e-02 - 8.40576952273409e-01 4.44816070395383e-02 - 8.55652758808818e-01 4.08761207109231e-02 - 8.70162898882712e-01 3.74269898462384e-02 - 8.84085033071272e-01 3.41426782029900e-02 - 8.97361214262371e-01 3.10259898674960e-02 - 9.09954680076662e-01 2.80965011913108e-02 - 9.21851471402547e-01 2.53449877379098e-02 - 9.33012836658427e-01 2.28002410570289e-02 - 9.43389278969050e-01 2.04521210438628e-02 - 9.52973153850560e-01 1.82952044665375e-02 - 9.61743130827061e-01 1.63215489515723e-02 - 9.69640690675464e-01 1.45391227290711e-02 - 9.76664215898664e-01 1.29559118724848e-02 - 9.82815077112014e-01 1.15715625438231e-02 - 9.88028440045103e-01 1.03940012922556e-02 - 9.92304836603751e-01 9.42728781931084e-03 - 9.95693518775914e-01 8.66223890894461e-03 - 9.98120489340015e-01 8.06680150452808e-03 - 9.99443037908705e-01 7.77257658160541e-03 - 1.00000000000000e+00 7.65904341792166e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_25.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_25.dat index e7fc1655..bcd2fa2f 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_25.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_25.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_25_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF25_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF25_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.826773 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.444318 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.680881 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.039875 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.875327 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.072181 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.008146 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085452 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.010481 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085918 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -2.02022174883932e-02 1.57417480797870e-02 4.90948732304041e-03 --1.77714285740401e+02 6.75136471732459e-02 1.96632475288215e-02 9.15116593168702e-02 --1.75428571400002e+02 1.35757437733690e-01 1.96507956897248e-02 1.82607426843221e-01 --1.73142857116900e+02 1.96420476265704e-01 2.00219153101846e-02 2.74705747357404e-01 --1.70857160423602e+02 2.52296141395312e-01 2.49473951094659e-02 3.65303939509748e-01 --1.68571631778825e+02 3.06425752668149e-01 3.77052830569853e-02 3.99400139052076e-01 --1.66285714267592e+02 3.62219619102148e-01 5.79260997741892e-02 3.97994909967673e-01 --1.63999999984490e+02 4.23067423909890e-01 8.43109802871185e-02 3.96546361970243e-01 --1.61714472886699e+02 4.92251414495777e-01 1.15563125156934e-01 3.95430425430436e-01 --1.59428371284127e+02 5.70682757977114e-01 1.50562013437243e-01 3.98802329555926e-01 --1.57142842639350e+02 6.50749297242347e-01 1.88842337379300e-01 4.15617140111983e-01 --1.54857313994574e+02 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0.00000000000000e+00 1.74928404489485e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_25_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_25_Coords.txt deleted file mode 100644 index 93b083b6..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_25_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.288390 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -6.54559549327049e-03 - 9.99429683992583e-01 -6.44732172236470e-03 - 9.98063017832965e-01 -6.21260046171728e-03 - 9.95573914266674e-01 -5.78796871753710e-03 - 9.92086309749559e-01 -5.19942584996543e-03 - 9.87686148675057e-01 -4.46420114537728e-03 - 9.82330525170640e-01 -3.59976620220949e-03 - 9.76011908335692e-01 -2.63948076106245e-03 - 9.68787467298381e-01 -1.62921202350643e-03 - 9.60674860259240e-01 -6.10249535995837e-04 - 9.51675358763677e-01 3.58708654796710e-04 - 9.41827652746244e-01 1.22851185585051e-03 - 9.31175295355131e-01 1.94620033547740e-03 - 9.19730397431178e-01 2.46607792235654e-03 - 9.07524559194720e-01 2.70176213503184e-03 - 8.94610408070308e-01 2.63987531633681e-03 - 8.81009696499435e-01 2.18266288695929e-03 - 8.66747905197194e-01 1.30548867724108e-03 - 8.51890258171205e-01 -4.94896826902933e-06 - 8.36469462621421e-01 -1.78188110518755e-03 - 8.20513485943698e-01 -4.04256268844746e-03 - 8.04073832217581e-01 -6.82933376727977e-03 - 7.87191529885653e-01 -1.01834076934459e-02 - 7.69897919101553e-01 -1.41582909820704e-02 - 7.52252341235159e-01 -1.87328941658398e-02 - 7.34291349178558e-01 -2.38459437886277e-02 - 7.16044924955764e-01 -2.94594777062382e-02 - 6.97571640033109e-01 -3.55192487989681e-02 - 6.78906186433687e-01 -4.19737467283325e-02 - 6.60080312620540e-01 -4.87450640495957e-02 - 6.41147517137212e-01 -5.57402808476912e-02 - 6.22137650968852e-01 -6.28619440563722e-02 - 6.03087998194415e-01 -7.00027861592005e-02 - 5.84045042118975e-01 -7.70738271978928e-02 - 5.65030897687003e-01 -8.39688563669667e-02 - 5.46088602779599e-01 -9.06147534941049e-02 - 5.27248673916899e-01 -9.69396128066641e-02 - 5.08535950506088e-01 -1.02898045253928e-01 - 4.89992355470388e-01 -1.08421329310341e-01 - 4.71632114506831e-01 -1.13485254920317e-01 - 4.53492503744347e-01 -1.18073079400668e-01 - 4.35593302897673e-01 -1.22169386286024e-01 - 4.17956065616942e-01 -1.25773309708254e-01 - 4.00609748442576e-01 -1.28906029687404e-01 - 3.83560931606009e-01 -1.31544579887329e-01 - 3.66843215733716e-01 -1.33718400329272e-01 - 3.50457316320503e-01 -1.35428190413669e-01 - 3.34434484008630e-01 -1.36700198298764e-01 - 3.18774100329315e-01 -1.37551916496642e-01 - 3.03499623121295e-01 -1.37992130849589e-01 - 2.88611293565648e-01 -1.38052414228809e-01 - 2.74124386665666e-01 -1.37748842632959e-01 - 2.60041455523719e-01 -1.37090328472676e-01 - 2.46374872015917e-01 -1.36106078672341e-01 - 2.33123443938834e-01 -1.34818862805255e-01 - 2.20293777810423e-01 -1.33228601101578e-01 - 2.07883282965331e-01 -1.31374749229383e-01 - 1.95902956391646e-01 -1.29261194122176e-01 - 1.84341253066628e-01 -1.26902036309226e-01 - 1.73213930954160e-01 -1.24323680417211e-01 - 1.62499176129638e-01 -1.21539888312170e-01 - 1.52214602777260e-01 -1.18581081849681e-01 - 1.42331759398971e-01 -1.15460050040984e-01 - 1.32872111539190e-01 -1.12190819990915e-01 - 1.23806439629760e-01 -1.08799564792637e-01 - 1.15147623386077e-01 -1.05296717526567e-01 - 1.06887208802748e-01 -1.01708814565723e-01 - 9.90071115215634e-02 -9.80450131967174e-02 - 9.15234043853439e-02 -9.43476090723471e-02 - 8.43970428172224e-02 -9.05910834299140e-02 - 7.76464790199521e-02 -8.68246327718549e-02 - 7.12479082120209e-02 -8.30354932464443e-02 - 6.51878662973747e-02 -7.92446842597681e-02 - 5.94874721274202e-02 -7.54707181227638e-02 - 5.41002464180900e-02 -7.17082996104204e-02 - 4.90378786701877e-02 -6.79992542145787e-02 - 4.43003497573338e-02 -6.43968615860198e-02 - 3.98423597346806e-02 -6.08363099235816e-02 - 3.56899752436130e-02 -5.73463636235250e-02 - 3.18292350050658e-02 -5.39281002328468e-02 - 2.82200072057899e-02 -5.05528624656306e-02 - 2.48925247792699e-02 -4.72621995119667e-02 - 2.18286683030034e-02 -4.40444967486072e-02 - 1.89846947131331e-02 -4.08692891315452e-02 - 1.63921917020335e-02 -3.77980887466518e-02 - 1.40446346341990e-02 -3.48608271357909e-02 - 1.18798249846349e-02 -3.19151969665709e-02 - 9.93094518736223e-03 -2.90300804019524e-02 - 8.21940795734749e-03 -2.62605409793478e-02 - 6.65838622137879e-03 -2.35102392493532e-02 - 5.26774192850643e-03 -2.08377928166547e-02 - 4.09515753852961e-03 -1.82776793691414e-02 - 3.09878859713640e-03 -1.58869595092834e-02 - 2.19660773551101e-03 -1.36952620124433e-02 - 1.46264176301869e-03 -1.13415365863304e-02 - 9.64484608297914e-04 -9.18041908695434e-03 - 5.99373867982851e-04 -6.60791363303032e-03 - 2.90086645599082e-04 -3.31347840473101e-03 - 7.80707788302466e-05 -8.63460344695060e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 9.70571117352938e-04 - 2.89878724192004e-04 4.02200831436448e-03 - 5.98775316682048e-04 8.05384176582453e-03 - 9.63326351634835e-04 1.06451737539178e-02 - 1.45966821282819e-03 1.31169096284725e-02 - 2.19097636449990e-03 1.57879417308201e-02 - 3.08997841959778e-03 1.86859479774245e-02 - 4.08271112470316e-03 2.14748916431365e-02 - 5.24853124383664e-03 2.42953581673576e-02 - 6.63128223001261e-03 2.72651475706036e-02 - 8.18368429859057e-03 3.02204336224934e-02 - 9.88361416849065e-03 3.31956290973824e-02 - 1.18176401547236e-02 3.63020512807022e-02 - 1.39661993216829e-02 3.94864128988147e-02 - 1.62951420791042e-02 4.26838135097491e-02 - 1.88631937781153e-02 4.59495896046058e-02 - 2.16807137532775e-02 4.92760846762566e-02 - 2.47159162958630e-02 5.26111934683339e-02 - 2.80064400105862e-02 5.59687930081278e-02 - 3.15762558914965e-02 5.94742819044633e-02 - 3.53948396168776e-02 6.30983765922562e-02 - 3.94949825480075e-02 6.67569120497318e-02 - 4.38979282781582e-02 7.04364779350461e-02 - 4.85758075737765e-02 7.40820009327883e-02 - 5.35679916138119e-02 7.77433018555094e-02 - 5.88818211488708e-02 8.13996025523519e-02 - 6.45001629027312e-02 8.50281975628155e-02 - 7.04692046391145e-02 8.86523846202040e-02 - 7.67740309924711e-02 9.22395693688524e-02 - 8.34162127168367e-02 9.57917901649779e-02 - 9.04290195190654e-02 9.92866536375970e-02 - 9.77906533229447e-02 1.02725111440533e-01 - 1.05536187198748e-01 1.06083870182156e-01 - 1.13658760041779e-01 1.09351385454245e-01 - 1.22161483318940e-01 1.12520113721477e-01 - 1.31067498602735e-01 1.15571017600703e-01 - 1.40354649921884e-01 1.18482528454386e-01 - 1.50055110786138e-01 1.21258757829951e-01 - 1.60148962661562e-01 1.23854687821563e-01 - 1.70658187899640e-01 1.26274012538587e-01 - 1.81574957422924e-01 1.28503917988260e-01 - 1.92907571409635e-01 1.30526833272342e-01 - 2.04657634577812e-01 1.32319751142055e-01 - 2.16817353069425e-01 1.33874173899348e-01 - 2.29396483963478e-01 1.35190939705454e-01 - 2.42377800694080e-01 1.36270192207215e-01 - 2.55773624268338e-01 1.37090515822444e-01 - 2.69566785632899e-01 1.37641343018519e-01 - 2.83765797226135e-01 1.37929233246561e-01 - 2.98347982887804e-01 1.37935845165962e-01 - 3.13318978785268e-01 1.37662803638892e-01 - 3.28658461892810e-01 1.37128881080005e-01 - 3.44364941645546e-01 1.36313688004779e-01 - 3.60419773725681e-01 1.35219685910056e-01 - 3.76811233766957e-01 1.33866204453081e-01 - 3.93525251020729e-01 1.32251835597055e-01 - 4.10538642553571e-01 1.30380975772261e-01 - 4.27843232490823e-01 1.28257654760212e-01 - 4.45406663468198e-01 1.25892965850202e-01 - 4.63222254103030e-01 1.23306127443924e-01 - 4.81251545655716e-01 1.20486190861226e-01 - 4.99481026671737e-01 1.17468675302073e-01 - 5.17879583085697e-01 1.14254809641812e-01 - 5.36417631367010e-01 1.10879200240641e-01 - 5.55075704909560e-01 1.07341212557386e-01 - 5.73808427242608e-01 1.03663508674709e-01 - 5.92596731105059e-01 9.98666003626047e-02 - 6.11401377553511e-01 9.59512815780360e-02 - 6.30186430605241e-01 9.19430440274983e-02 - 6.48926781663159e-01 8.78580813759376e-02 - 6.67570206424973e-01 8.37212010300814e-02 - 6.86088429590952e-01 7.95496431374060e-02 - 7.04445389043917e-01 7.53527739103750e-02 - 7.22592093722966e-01 7.11567787003146e-02 - 7.40501800453524e-01 6.69831861848776e-02 - 7.58125457122835e-01 6.28487710088958e-02 - 7.75421014376153e-01 5.87695602397671e-02 - 7.92362373587600e-01 5.47724368004539e-02 - 8.08894546151696e-01 5.08629411689835e-02 - 8.24974633014891e-01 4.70613329836886e-02 - 8.40576952273409e-01 4.33920671856691e-02 - 8.55652758808818e-01 3.98474235488448e-02 - 8.70162898882712e-01 3.64559301642452e-02 - 8.84085033071272e-01 3.32283149993398e-02 - 8.97361214262371e-01 3.01650162724121e-02 - 9.09954680076662e-01 2.72864886596757e-02 - 9.21851471402547e-01 2.45796297654421e-02 - 9.33012836658427e-01 2.20766306741178e-02 - 9.43389278969050e-01 1.97670382525268e-02 - 9.52973153850560e-01 1.76471434528119e-02 - 9.61743130827061e-01 1.57068238750744e-02 - 9.69640690675464e-01 1.39520075046613e-02 - 9.76664215898664e-01 1.23927569642349e-02 - 9.82815077112014e-01 1.10292449574873e-02 - 9.88028440045103e-01 9.86739191786453e-03 - 9.92304836603751e-01 8.91293396978775e-03 - 9.95693518775914e-01 8.15768635592600e-03 - 9.98120489340015e-01 7.59868541723245e-03 - 9.99443037908705e-01 7.30574633636735e-03 - 1.00000000000000e+00 7.18638277077981e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_26.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_26.dat index 7c4833ca..4590fcd3 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_26.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_26.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_26_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF26_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF26_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.851792 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.482875 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.666446 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.040731 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.861101 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.068737 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.007711 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085444 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.010088 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085961 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -2.33847962008625e-02 1.45307285310868e-02 4.90966610678082e-03 --1.77714285740401e+02 6.75699288188731e-02 1.83796674984792e-02 9.15114179879664e-02 --1.75428571400002e+02 1.35819305485632e-01 1.83633524593176e-02 1.82609561512334e-01 --1.73142857116900e+02 1.95421577969269e-01 1.87227855935343e-02 2.74694720030434e-01 --1.70857160423602e+02 2.49883770058836e-01 2.37267491233323e-02 3.65330397237567e-01 --1.68571631778825e+02 3.02709808405397e-01 3.67110438663285e-02 3.98906236216804e-01 --1.66285714267592e+02 3.57420084218524e-01 5.72902431472063e-02 3.96739448713881e-01 --1.63999999984490e+02 4.17508250169778e-01 8.41384236714374e-02 3.94658162647513e-01 --1.61714472886699e+02 4.86480356594216e-01 1.15932870876900e-01 3.92630820086789e-01 --1.59428371284127e+02 5.65584440474650e-01 1.51537088829980e-01 3.95561349180008e-01 --1.57142842639350e+02 6.46866395812599e-01 1.90478496891938e-01 4.12429985451927e-01 --1.54857313994574e+02 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0.00000000000000e+00 1.58679141491202e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_26_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_26_Coords.txt deleted file mode 100644 index f5a0f35e..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_26_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.287823 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -5.94000000000000e-03 - 9.99429683992583e-01 -5.84639401370242e-03 - 9.98063017832965e-01 -5.62253285424618e-03 - 9.95573914266674e-01 -5.21645462305230e-03 - 9.92086309749559e-01 -4.65106911349205e-03 - 9.87686148675057e-01 -3.93926560568960e-03 - 9.82330525170640e-01 -3.09716674966862e-03 - 9.76011908335692e-01 -2.15719415680774e-03 - 9.68787467298381e-01 -1.16385144150018e-03 - 9.60674860259240e-01 -1.57286242674071e-04 - 9.51675358763677e-01 8.04281128686971e-04 - 9.41827652746244e-01 1.67595431006768e-03 - 9.31175295355131e-01 2.41506307674754e-03 - 9.19730397431178e-01 2.96968164182150e-03 - 9.07524559194720e-01 3.24980870975447e-03 - 8.94610408070308e-01 3.23672486596825e-03 - 8.81009696499435e-01 2.84395862761580e-03 - 8.66747905197194e-01 2.04259942446387e-03 - 8.51890258171205e-01 8.22760212589218e-04 - 8.36469462621421e-01 -8.52636428842255e-04 - 8.20513485943698e-01 -2.99886415375106e-03 - 8.04073832217581e-01 -5.66141893951599e-03 - 7.87191529885653e-01 -8.88698645944340e-03 - 7.69897919101553e-01 -1.27267457934198e-02 - 7.52252341235159e-01 -1.71634970553800e-02 - 7.34291349178558e-01 -2.21420045141886e-02 - 7.16044924955764e-01 -2.76214938661734e-02 - 6.97571640033109e-01 -3.35464555473090e-02 - 6.78906186433687e-01 -3.98695923297235e-02 - 6.60080312620540e-01 -4.65136897532947e-02 - 6.41147517137212e-01 -5.33894180542301e-02 - 6.22137650968852e-01 -6.03974946053398e-02 - 6.03087998194415e-01 -6.74292859942025e-02 - 5.84045042118975e-01 -7.44015982279818e-02 - 5.65030897687003e-01 -8.12029111350930e-02 - 5.46088602779599e-01 -8.77603619993322e-02 - 5.27248673916899e-01 -9.40042609350062e-02 - 5.08535950506088e-01 -9.98868686323100e-02 - 4.89992355470388e-01 -1.05337276803669e-01 - 4.71632114506831e-01 -1.10330871984436e-01 - 4.53492503744347e-01 -1.14852043692364e-01 - 4.35593302897673e-01 -1.18882775742242e-01 - 4.17956065616942e-01 -1.22422404650662e-01 - 4.00609748442576e-01 -1.25494451518036e-01 - 3.83560931606009e-01 -1.28076555649304e-01 - 3.66843215733716e-01 -1.30195362744447e-01 - 3.50457316320503e-01 -1.31854722649703e-01 - 3.34434484008630e-01 -1.33080693043705e-01 - 3.18774100329315e-01 -1.33893356629609e-01 - 3.03499623121295e-01 -1.34295366554817e-01 - 2.88611293565648e-01 -1.34326289624709e-01 - 2.74124386665666e-01 -1.33995780576984e-01 - 2.60041455523719e-01 -1.33320116559377e-01 - 2.46374872015917e-01 -1.32321465328448e-01 - 2.33123443938834e-01 -1.31028268975345e-01 - 2.20293777810423e-01 -1.29437942753933e-01 - 2.07883282965331e-01 -1.27589977380036e-01 - 1.95902956391646e-01 -1.25489143702241e-01 - 1.84341253066628e-01 -1.23147723208678e-01 - 1.73213930954160e-01 -1.20593690589943e-01 - 1.62499176129638e-01 -1.17841553683024e-01 - 1.52214602777260e-01 -1.14921836030391e-01 - 1.42331759398971e-01 -1.11845191654168e-01 - 1.32872111539190e-01 -1.08626382940671e-01 - 1.23806439629760e-01 -1.05293081224446e-01 - 1.15147623386077e-01 -1.01851966675519e-01 - 1.06887208802748e-01 -9.83319780133132e-02 - 9.90071115215634e-02 -9.47417262910496e-02 - 9.15234043853439e-02 -9.11228668502375e-02 - 8.43970428172224e-02 -8.74484213537215e-02 - 7.76464790199521e-02 -8.37685550366159e-02 - 7.12479082120209e-02 -8.00678835528577e-02 - 6.51878662973747e-02 -7.63693823107186e-02 - 5.94874721274202e-02 -7.26896228185098e-02 - 5.41002464180900e-02 -6.90235957088213e-02 - 4.90378786701877e-02 -6.54155349565695e-02 - 4.43003497573338e-02 -6.19198166686688e-02 - 3.98423597346806e-02 -5.84685698277760e-02 - 3.56899752436130e-02 -5.50879030708543e-02 - 3.18292350050658e-02 -5.17792636346292e-02 - 2.82200072057899e-02 -4.85125120598106e-02 - 2.48925247792699e-02 -4.53317967071806e-02 - 2.18286683030034e-02 -4.22220336213642e-02 - 1.89846947131331e-02 -3.91597839738936e-02 - 1.63921917020335e-02 -3.62011493651813e-02 - 1.40446346341990e-02 -3.33745625547637e-02 - 1.18798249846349e-02 -3.05395098410090e-02 - 9.93094518736223e-03 -2.77611220880847e-02 - 8.21940795734749e-03 -2.50959425887954e-02 - 6.65838622137879e-03 -2.24494778082409e-02 - 5.26774192850643e-03 -1.99047458925708e-02 - 4.09515753852961e-03 -1.74758877811077e-02 - 3.09878859713640e-03 -1.51814742249559e-02 - 2.19660773551101e-03 -1.30278896026934e-02 - 1.46264176301869e-03 -1.07211212434447e-02 - 9.64484608297914e-04 -8.62165579045941e-03 - 5.99373867982851e-04 -6.23785529140956e-03 - 2.90086645599082e-04 -3.18268079764547e-03 - 7.80707788302466e-05 -8.57238689135622e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 9.36355967408960e-04 - 2.89878724192004e-04 3.99465044565100e-03 - 5.98775316682048e-04 7.95290107817943e-03 - 9.63326351634835e-04 1.03349166911548e-02 - 1.45966821282819e-03 1.27436707683507e-02 - 2.19097636449990e-03 1.53501619436709e-02 - 3.08997841959778e-03 1.82239914062947e-02 - 4.08271112470316e-03 2.09358986881850e-02 - 5.24853124383664e-03 2.36824161977725e-02 - 6.63128223001261e-03 2.65867435255985e-02 - 8.18368429859057e-03 2.94574978415561e-02 - 9.88361416849065e-03 3.23503904515495e-02 - 1.18176401547236e-02 3.53802539138142e-02 - 1.39661993216829e-02 3.84826973794658e-02 - 1.62951420791042e-02 4.16008064262210e-02 - 1.88631937781153e-02 4.47879749676627e-02 - 2.16807137532775e-02 4.80348315385361e-02 - 2.47159162958630e-02 5.12909762923480e-02 - 2.80064400105862e-02 5.45680544767200e-02 - 3.15762558914965e-02 5.79948192913181e-02 - 3.53948396168776e-02 6.15446167988168e-02 - 3.94949825480075e-02 6.51301451765064e-02 - 4.38979282781582e-02 6.87368522780402e-02 - 4.85758075737765e-02 7.23095515318872e-02 - 5.35679916138119e-02 7.58983887633071e-02 - 5.88818211488708e-02 7.94842019619319e-02 - 6.45001629027312e-02 8.30454444419434e-02 - 7.04692046391145e-02 8.66036961253093e-02 - 7.67740309924711e-02 9.01266450662800e-02 - 8.34162127168367e-02 9.36173751576571e-02 - 9.04290195190654e-02 9.70543753941137e-02 - 9.77906533229447e-02 1.00438686653847e-01 - 1.05536187198748e-01 1.03746852731756e-01 - 1.13658760041779e-01 1.06969622507395e-01 - 1.22161483318940e-01 1.10097861407274e-01 - 1.31067498602735e-01 1.13114452033838e-01 - 1.40354649921884e-01 1.15996545911172e-01 - 1.50055110786138e-01 1.18749594805733e-01 - 1.60148962661562e-01 1.21327266082135e-01 - 1.70658187899640e-01 1.23735057422375e-01 - 1.81574957422924e-01 1.25960254203734e-01 - 1.92907571409635e-01 1.27985721471221e-01 - 2.04657634577812e-01 1.29785750458718e-01 - 2.16817353069425e-01 1.31353766055536e-01 - 2.29396483963478e-01 1.32690192568824e-01 - 2.42377800694080e-01 1.33793646076068e-01 - 2.55773624268338e-01 1.34641221410344e-01 - 2.69566785632899e-01 1.35222819070152e-01 - 2.83765797226135e-01 1.35544531016931e-01 - 2.98347982887804e-01 1.35584425808391e-01 - 3.13318978785268e-01 1.35347949874126e-01 - 3.28658461892810e-01 1.34849573029271e-01 - 3.44364941645546e-01 1.34069133872330e-01 - 3.60419773725681e-01 1.33009196624718e-01 - 3.76811233766957e-01 1.31691017970649e-01 - 3.93525251020729e-01 1.30110439886585e-01 - 4.10538642553571e-01 1.28277034213244e-01 - 4.27843232490823e-01 1.26189726782214e-01 - 4.45406663468198e-01 1.23861165555701e-01 - 4.63222254103030e-01 1.21310683921327e-01 - 4.81251545655716e-01 1.18529091879235e-01 - 4.99481026671737e-01 1.15548436492766e-01 - 5.17879583085697e-01 1.12374047168208e-01 - 5.36417631367010e-01 1.09036592956659e-01 - 5.55075704909560e-01 1.05534424993944e-01 - 5.73808427242608e-01 1.01893385103438e-01 - 5.92596731105059e-01 9.81335125765603e-02 - 6.11401377553511e-01 9.42543247646393e-02 - 6.30186430605241e-01 9.02823136833599e-02 - 6.48926781663159e-01 8.62345531733664e-02 - 6.67570206424973e-01 8.21366521324646e-02 - 6.86088429590952e-01 7.80085789028711e-02 - 7.04445389043917e-01 7.38555268402751e-02 - 7.22592093722966e-01 6.97077433635793e-02 - 7.40501800453524e-01 6.55844369077509e-02 - 7.58125457122835e-01 6.15029776706917e-02 - 7.75421014376153e-01 5.74783934681392e-02 - 7.92362373587600e-01 5.35369933121430e-02 - 8.08894546151696e-01 4.96835753698652e-02 - 8.24974633014891e-01 4.59409811433649e-02 - 8.40576952273409e-01 4.23295419862284e-02 - 8.55652758808818e-01 3.88419885388313e-02 - 8.70162898882712e-01 3.55049426119077e-02 - 8.84085033071272e-01 3.23301284223988e-02 - 8.97361214262371e-01 2.93179056422943e-02 - 9.09954680076662e-01 2.64868433371973e-02 - 9.21851471402547e-01 2.38237032689966e-02 - 9.33012836658427e-01 2.13601667226618e-02 - 9.43389278969050e-01 1.90872126876703e-02 - 9.52973153850560e-01 1.70014391961382e-02 - 9.61743130827061e-01 1.50921171985088e-02 - 9.69640690675464e-01 1.33643352955622e-02 - 9.76664215898664e-01 1.18288196445189e-02 - 9.82815077112014e-01 1.04859728683476e-02 - 9.88028440045103e-01 9.34093708322004e-03 - 9.92304836603751e-01 8.40004545500557e-03 - 9.95693518775914e-01 7.65556665124824e-03 - 9.98120489340015e-01 7.12260533946481e-03 - 9.99443037908705e-01 6.83225660100113e-03 - 1.00000000000000e+00 6.71000000000000e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_27.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_27.dat index f07f4571..a84e7d2f 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_27.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_27.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_27_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF27_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF27_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.854288 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.497773 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.673302 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.037022 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.852284 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.062830 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.007391 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085560 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.009710 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085908 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -2.00051396010153e-02 1.36712158299644e-02 4.91091215283908e-03 --1.77714285740401e+02 6.71576770905890e-02 1.74299051083258e-02 9.15152582342736e-02 --1.75428571400002e+02 1.34996019608565e-01 1.73887445980226e-02 1.82596168282205e-01 --1.73142857116900e+02 1.93571530780434e-01 1.76526856718765e-02 2.74725195623310e-01 --1.70857160423602e+02 2.46955665035588e-01 2.26387919581735e-02 3.65285247054120e-01 --1.68571631778825e+02 2.98924305983313e-01 3.57811554995682e-02 3.98374551391917e-01 --1.66285714267592e+02 3.52888737614894e-01 5.66816496764848e-02 3.95353589736573e-01 --1.63999999984490e+02 4.12234077516403e-01 8.39810680184157e-02 3.92309749706650e-01 --1.61714472886699e+02 4.80483503595436e-01 1.16221905252562e-01 3.89498590446283e-01 --1.59428371284127e+02 5.59164322900866e-01 1.52308222612832e-01 3.91758680175433e-01 --1.57142842639350e+02 6.40475208310696e-01 1.91802670706766e-01 4.08700408344513e-01 --1.54857313994574e+02 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0.00000000000000e+00 1.47317105498312e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_27_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_27_Coords.txt deleted file mode 100644 index e67aa7d5..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_27_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.287851 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -5.36518357884113e-03 - 9.99429683992583e-01 -5.27397369913001e-03 - 9.98063017832965e-01 -5.05594682134402e-03 - 9.95573914266674e-01 -4.66077650352731e-03 - 9.92086309749559e-01 -4.11109017295554e-03 - 9.87686148675057e-01 -3.41980617584124e-03 - 9.82330525170640e-01 -2.60146741194483e-03 - 9.76011908335692e-01 -1.68589711287293e-03 - 9.68787467298381e-01 -7.14442892982645e-04 - 9.60674860259240e-01 2.76146027026378e-04 - 9.51675358763677e-01 1.23344378663880e-03 - 9.41827652746244e-01 2.11739078131049e-03 - 9.31175295355131e-01 2.87875943340349e-03 - 9.19730397431178e-01 3.46594422118492e-03 - 9.07524559194720e-01 3.79082490960566e-03 - 8.94610408070308e-01 3.82365118524085e-03 - 8.81009696499435e-01 3.49310843290742e-03 - 8.66747905197194e-01 2.76266729261935e-03 - 8.51890258171205e-01 1.62868223268420e-03 - 8.36469462621421e-01 5.20611616075879e-05 - 8.20513485943698e-01 -1.98553866113997e-03 - 8.04073832217581e-01 -4.52764817548329e-03 - 7.87191529885653e-01 -7.62742349348973e-03 - 7.69897919101553e-01 -1.13337454145990e-02 - 7.52252341235159e-01 -1.56329215986144e-02 - 7.34291349178558e-01 -2.04762018659025e-02 - 7.16044924955764e-01 -2.58181652632749e-02 - 6.97571640033109e-01 -3.16049143584676e-02 - 6.78906186433687e-01 -3.77918226434121e-02 - 6.60080312620540e-01 -4.43030877674059e-02 - 6.41147517137212e-01 -5.10513304984711e-02 - 6.22137650968852e-01 -5.79370642063588e-02 - 6.03087998194415e-01 -6.48519158169489e-02 - 5.84045042118975e-01 -7.17145318248799e-02 - 5.65030897687003e-01 -7.84143482599765e-02 - 5.46088602779599e-01 -8.48769963133521e-02 - 5.27248673916899e-01 -9.10339714267079e-02 - 5.08535950506088e-01 -9.68336456637784e-02 - 4.89992355470388e-01 -1.02209203048663e-01 - 4.71632114506831e-01 -1.07131666068788e-01 - 4.53492503744347e-01 -1.11583869819670e-01 - 4.35593302897673e-01 -1.15547290786575e-01 - 4.17956065616942e-01 -1.19024185413527e-01 - 4.00609748442576e-01 -1.22033596677402e-01 - 3.83560931606009e-01 -1.24560802239458e-01 - 3.66843215733716e-01 -1.26626107038211e-01 - 3.50457316320503e-01 -1.28237123510453e-01 - 3.34434484008630e-01 -1.29419016563679e-01 - 3.18774100329315e-01 -1.30194401599784e-01 - 3.03499623121295e-01 -1.30562615721753e-01 - 2.88611293565648e-01 -1.30568015718197e-01 - 2.74124386665666e-01 -1.30214033388010e-01 - 2.60041455523719e-01 -1.29525696352148e-01 - 2.46374872015917e-01 -1.28518790550968e-01 - 2.33123443938834e-01 -1.27225164713058e-01 - 2.20293777810423e-01 -1.25643141783464e-01 - 2.07883282965331e-01 -1.23807424520546e-01 - 1.95902956391646e-01 -1.21727934132866e-01 - 1.84341253066628e-01 -1.19413870239405e-01 - 1.73213930954160e-01 -1.16895850240117e-01 - 1.62499176129638e-01 -1.14186321793004e-01 - 1.52214602777260e-01 -1.11316099049234e-01 - 1.42331759398971e-01 -1.08294690430477e-01 - 1.32872111539190e-01 -1.05139600452333e-01 - 1.23806439629760e-01 -1.01875693126241e-01 - 1.15147623386077e-01 -9.85095507942617e-02 - 1.06887208802748e-01 -9.50709166343000e-02 - 9.90071115215634e-02 -9.15666870997439e-02 - 9.15234043853439e-02 -8.80375859414276e-02 - 8.43970428172224e-02 -8.44598986400463e-02 - 7.76464790199521e-02 -8.08788178997442e-02 - 7.12479082120209e-02 -7.72824830317068e-02 - 6.51878662973747e-02 -7.36916631405216e-02 - 5.94874721274202e-02 -7.01220868049324e-02 - 5.41002464180900e-02 -6.65699416114887e-02 - 4.90378786701877e-02 -6.30772512798635e-02 - 4.43003497573338e-02 -5.96915958175961e-02 - 3.98423597346806e-02 -5.63512591392342e-02 - 3.56899752436130e-02 -5.30806151866037e-02 - 3.18292350050658e-02 -4.98820484131329e-02 - 2.82200072057899e-02 -4.67248026566113e-02 - 2.48925247792699e-02 -4.36545075387669e-02 - 2.18286683030034e-02 -4.06542310753119e-02 - 1.89846947131331e-02 -3.77061119308619e-02 - 1.63921917020335e-02 -3.48607910464865e-02 - 1.40446346341990e-02 -3.21330067786162e-02 - 1.18798249846349e-02 -2.94013967132557e-02 - 9.93094518736223e-03 -2.67296810209405e-02 - 8.21940795734749e-03 -2.41643167038216e-02 - 6.65838622137879e-03 -2.16122768236219e-02 - 5.26774192850643e-03 -1.92053887995105e-02 - 4.09515753852961e-03 -1.69168596326561e-02 - 3.09878859713640e-03 -1.47133582401055e-02 - 2.19660773551101e-03 -1.25683799489063e-02 - 1.46264176301869e-03 -1.02500276081168e-02 - 9.64484608297914e-04 -8.08770509728914e-03 - 5.99373867982851e-04 -5.78574061162076e-03 - 2.90086645599082e-04 -2.97169962011518e-03 - 7.80707788302466e-05 -8.24625374210416e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 8.64168110479416e-04 - 2.89878724192004e-04 3.78066225793185e-03 - 5.98775316682048e-04 7.55627887803577e-03 - 9.63326351634835e-04 9.87931001806894e-03 - 1.45966821282819e-03 1.23310135823986e-02 - 2.19097636449990e-03 1.49250558289557e-02 - 3.08997841959778e-03 1.77611774036326e-02 - 4.08271112470316e-03 2.03940629241338e-02 - 5.24853124383664e-03 2.30735613278049e-02 - 6.63128223001261e-03 2.59234070535173e-02 - 8.18368429859057e-03 2.87271330835638e-02 - 9.88361416849065e-03 3.15459382412664e-02 - 1.18176401547236e-02 3.45123575626723e-02 - 1.39661993216829e-02 3.75461942816409e-02 - 1.62951420791042e-02 4.05946679702928e-02 - 1.88631937781153e-02 4.37171766537522e-02 - 2.16807137532775e-02 4.68988813748891e-02 - 2.47159162958630e-02 5.00911346543662e-02 - 2.80064400105862e-02 5.33055302651913e-02 - 3.15762558914965e-02 5.66548887168090e-02 - 3.53948396168776e-02 6.01161971454907e-02 - 3.94949825480075e-02 6.36138814092407e-02 - 4.38979282781582e-02 6.71360786203061e-02 - 4.85758075737765e-02 7.06298672123588e-02 - 5.35679916138119e-02 7.41404961581447e-02 - 5.88818211488708e-02 7.76512029123671e-02 - 6.45001629027312e-02 8.11422012800448e-02 - 7.04692046391145e-02 8.46321326666455e-02 - 7.67740309924711e-02 8.80902012712424e-02 - 8.34162127168367e-02 9.15179870368885e-02 - 9.04290195190654e-02 9.48979356721603e-02 - 9.77906533229447e-02 9.82274499028523e-02 - 1.05536187198748e-01 1.01485803386470e-01 - 1.13658760041779e-01 1.04663515584506e-01 - 1.22161483318940e-01 1.07751449219725e-01 - 1.31067498602735e-01 1.10734416198965e-01 - 1.40354649921884e-01 1.13588916484409e-01 - 1.50055110786138e-01 1.16317506931801e-01 - 1.60148962661562e-01 1.18878010542390e-01 - 1.70658187899640e-01 1.21277562622828e-01 - 1.81574957422924e-01 1.23498432953504e-01 - 1.92907571409635e-01 1.25526036077852e-01 - 2.04657634577812e-01 1.27335039610886e-01 - 2.16817353069425e-01 1.28918304502155e-01 - 2.29396483963478e-01 1.30274464933414e-01 - 2.42377800694080e-01 1.31400891794919e-01 - 2.55773624268338e-01 1.32276151267998e-01 - 2.69566785632899e-01 1.32890452805121e-01 - 2.83765797226135e-01 1.33242770193019e-01 - 2.98347982887804e-01 1.33314714297919e-01 - 3.13318978785268e-01 1.33114365458219e-01 - 3.28658461892810e-01 1.32645436255805e-01 - 3.44364941645546e-01 1.31899191876642e-01 - 3.60419773725681e-01 1.30871406716726e-01 - 3.76811233766957e-01 1.29585560408410e-01 - 3.93525251020729e-01 1.28036604338915e-01 - 4.10538642553571e-01 1.26237992511117e-01 - 4.27843232490823e-01 1.24183723002737e-01 - 4.45406663468198e-01 1.21890320807401e-01 - 4.63222254103030e-01 1.19373148211947e-01 - 4.81251545655716e-01 1.16629737888778e-01 - 4.99481026671737e-01 1.13683019464519e-01 - 5.17879583085697e-01 1.10544671283192e-01 - 5.36417631367010e-01 1.07242351655847e-01 - 5.55075704909560e-01 1.03775546064841e-01 - 5.73808427242608e-01 1.00168606009869e-01 - 5.92596731105059e-01 9.64417014819913e-02 - 6.11401377553511e-01 9.25969779555228e-02 - 6.30186430605241e-01 8.86585949139805e-02 - 6.48926781663159e-01 8.46463693981055e-02 - 6.67570206424973e-01 8.05846920956089e-02 - 6.86088429590952e-01 7.64957994277859e-02 - 7.04445389043917e-01 7.23859455725189e-02 - 7.22592093722966e-01 6.82832879070323e-02 - 7.40501800453524e-01 6.42060866181910e-02 - 7.58125457122835e-01 6.01749090656705e-02 - 7.75421014376153e-01 5.62030634993235e-02 - 7.92362373587600e-01 5.23148364799964e-02 - 8.08894546151696e-01 4.85160609301197e-02 - 8.24974633014891e-01 4.48309128592449e-02 - 8.40576952273409e-01 4.12741665374757e-02 - 8.55652758808818e-01 3.78424042225391e-02 - 8.70162898882712e-01 3.45588642680053e-02 - 8.84085033071272e-01 3.14344066051356e-02 - 8.97361214262371e-01 2.84727950975867e-02 - 9.09954680076662e-01 2.56865403953306e-02 - 9.21851471402547e-01 2.30674434339674e-02 - 9.33012836658427e-01 2.06414510887446e-02 - 9.43389278969050e-01 1.84036335474913e-02 - 9.52973153850560e-01 1.63487212125285e-02 - 9.61743130827061e-01 1.44676442779181e-02 - 9.69640690675464e-01 1.27660673152448e-02 - 9.76664215898664e-01 1.12536841155133e-02 - 9.82815077112014e-01 9.93084577503022e-03 - 9.88028440045103e-01 8.80341937046565e-03 - 9.92304836603751e-01 7.87711519422892e-03 - 9.95693518775914e-01 7.14406385081021e-03 - 9.98120489340015e-01 6.62611417141696e-03 - 9.99443037908705e-01 6.33957067994971e-03 - 1.00000000000000e+00 6.21741113949155e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_28.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_28.dat index fabe242d..06a7ba4d 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_28.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_28.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_28_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF28_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF28_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.850522 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.458884 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.689325 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.028392 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.845663 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.048830 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.007098 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085701 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.009329 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085825 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -1.21070490968245e-02 1.28917799873893e-02 4.91348961496877e-03 --1.77714285740401e+02 6.61257233732894e-02 1.65566853268865e-02 9.15242327001687e-02 --1.75428571400002e+02 1.32935482678395e-01 1.64861568760618e-02 1.82564868965077e-01 --1.73142857116900e+02 1.90779092112778e-01 1.66287143269466e-02 2.74796415578235e-01 --1.70857160423602e+02 2.43633109767278e-01 2.15579569604867e-02 3.65179733306019e-01 --1.68571631778825e+02 2.95155801339450e-01 3.48313826166897e-02 3.97812617621364e-01 --1.66285714267592e+02 3.48611255120615e-01 5.60491965684842e-02 3.93854492849511e-01 --1.63999999984490e+02 4.07238653257070e-01 8.38197146380805e-02 3.89533088318959e-01 --1.61714472886699e+02 4.74424703595679e-01 1.16456673168300e-01 3.86080521360324e-01 --1.59428371284127e+02 5.51666025666556e-01 1.52958359097067e-01 3.87453933660840e-01 --1.57142842639350e+02 6.31469680794292e-01 1.92966054435379e-01 4.04500288674221e-01 --1.54857313994574e+02 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0.00000000000000e+00 1.36543508227385e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_28_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_28_Coords.txt deleted file mode 100644 index 6592c7b4..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_28_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.287986 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -4.81546339449945e-03 - 9.99429683992583e-01 -4.72472805573164e-03 - 9.98063017832965e-01 -4.50817579432570e-03 - 9.95573914266674e-01 -4.11691224456629e-03 - 9.92086309749559e-01 -3.57531128215982e-03 - 9.87686148675057e-01 -2.89956130917134e-03 - 9.82330525170640e-01 -2.10281037396659e-03 - 9.76011908335692e-01 -1.21152719003242e-03 - 9.68787467298381e-01 -2.63051006238450e-04 - 9.60674860259240e-01 7.10317593907367e-04 - 9.51675358763677e-01 1.66590948076643e-03 - 9.41827652746244e-01 2.56995189553180e-03 - 9.31175295355131e-01 3.35586196590182e-03 - 9.19730397431178e-01 3.97672128994541e-03 - 9.07524559194720e-01 4.35023621718402e-03 - 8.94610408070308e-01 4.42942325343571e-03 - 8.81009696499435e-01 4.16303813571203e-03 - 8.66747905197194e-01 3.50326593955241e-03 - 8.51890258171205e-01 2.45509925675673e-03 - 8.36469462621421e-01 9.78072961403676e-04 - 8.20513485943698e-01 -9.52072489857552e-04 - 8.04073832217581e-01 -3.37390430321953e-03 - 7.87191529885653e-01 -6.34811697331111e-03 - 7.69897919101553e-01 -9.92074399575575e-03 - 7.52252341235159e-01 -1.40817507633793e-02 - 7.34291349178558e-01 -1.87897680323150e-02 - 7.16044924955764e-01 -2.39921570625168e-02 - 6.97571640033109e-01 -2.96381491001812e-02 - 6.78906186433687e-01 -3.56851927605324e-02 - 6.60080312620540e-01 -4.20587177603381e-02 - 6.41147517137212e-01 -4.86725407895057e-02 - 6.22137650968852e-01 -5.54277724093834e-02 - 6.03087998194415e-01 -6.22176123248820e-02 - 5.84045042118975e-01 -6.89605948847067e-02 - 5.65030897687003e-01 -7.55512206802970e-02 - 5.46088602779599e-01 -8.19125588066241e-02 - 5.27248673916899e-01 -8.79767999133520e-02 - 5.08535950506088e-01 -9.36869282238718e-02 - 4.89992355470388e-01 -9.89856249152761e-02 - 4.71632114506831e-01 -1.03836357948547e-01 - 4.53492503744347e-01 -1.08218088168089e-01 - 4.35593302897673e-01 -1.12113080319200e-01 - 4.17956065616942e-01 -1.15528531544352e-01 - 4.00609748442576e-01 -1.18473479711362e-01 - 3.83560931606009e-01 -1.20947225371183e-01 - 3.66843215733716e-01 -1.22959989936954e-01 - 3.50457316320503e-01 -1.24524450195287e-01 - 3.34434484008630e-01 -1.25664139382834e-01 - 3.18774100329315e-01 -1.26404459460489e-01 - 3.03499623121295e-01 -1.26742902547085e-01 - 2.88611293565648e-01 -1.26727121749309e-01 - 2.74124386665666e-01 -1.26353286088332e-01 - 2.60041455523719e-01 -1.25657673889619e-01 - 2.46374872015917e-01 -1.24648888972259e-01 - 2.33123443938834e-01 -1.23361373119739e-01 - 2.20293777810423e-01 -1.21796791541088e-01 - 2.07883282965331e-01 -1.19980898400917e-01 - 1.95902956391646e-01 -1.17932687770471e-01 - 1.84341253066628e-01 -1.15656871112422e-01 - 1.73213930954160e-01 -1.13187804626897e-01 - 1.62499176129638e-01 -1.10533635032055e-01 - 1.52214602777260e-01 -1.07725374119360e-01 - 1.42331759398971e-01 -1.04771949141255e-01 - 1.32872111539190e-01 -1.01695145977261e-01 - 1.23806439629760e-01 -9.85138823507804e-02 - 1.15147623386077e-01 -9.52370310122420e-02 - 1.06887208802748e-01 -9.18939724236507e-02 - 9.90071115215634e-02 -8.84890357964356e-02 - 9.15234043853439e-02 -8.50615163364889e-02 - 8.43970428172224e-02 -8.15942320156592e-02 - 7.76464790199521e-02 -7.81232220905221e-02 - 7.12479082120209e-02 -7.46441533422106e-02 - 6.51878662973747e-02 -7.11728309584587e-02 - 5.94874721274202e-02 -6.77247455609481e-02 - 5.41002464180900e-02 -6.42979221955292e-02 - 4.90378786701877e-02 -6.09295694268874e-02 - 4.43003497573338e-02 -5.76559604562196e-02 - 3.98423597346806e-02 -5.44269880918347e-02 - 3.56899752436130e-02 -5.12657861371263e-02 - 3.18292350050658e-02 -4.81760535616419e-02 - 2.82200072057899e-02 -4.51266138159832e-02 - 2.48925247792699e-02 -4.21644523858152e-02 - 2.18286683030034e-02 -3.92712495741261e-02 - 1.89846947131331e-02 -3.64347887589701e-02 - 1.63921917020335e-02 -3.36998954621667e-02 - 1.40446346341990e-02 -3.10615283350594e-02 - 1.18798249846349e-02 -2.84259914447209e-02 - 9.93094518736223e-03 -2.58567117033677e-02 - 8.21940795734749e-03 -2.33839749597704e-02 - 6.65838622137879e-03 -2.09150676252876e-02 - 5.26774192850643e-03 -1.86442340781365e-02 - 4.09515753852961e-03 -1.64930359530963e-02 - 3.09878859713640e-03 -1.43704778258076e-02 - 2.19660773551101e-03 -1.22142401305146e-02 - 1.46264176301869e-03 -9.84873973150391e-03 - 9.64484608297914e-04 -7.53581809577439e-03 - 5.99373867982851e-04 -5.24104898082843e-03 - 2.90086645599082e-04 -2.66900477488067e-03 - 7.80707788302466e-05 -7.44779821041564e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 7.61645489206473e-04 - 2.89878724192004e-04 3.33326708009986e-03 - 5.98775316682048e-04 6.79585249012019e-03 - 9.63326351634835e-04 9.28260501479058e-03 - 1.45966821282819e-03 1.18859515206369e-02 - 2.19097636449990e-03 1.45107872216291e-02 - 3.08997841959778e-03 1.73110699764758e-02 - 4.08271112470316e-03 1.98689832850759e-02 - 5.24853124383664e-03 2.24915472762164e-02 - 6.63128223001261e-03 2.52991879248929e-02 - 8.18368429859057e-03 2.80495240584492e-02 - 9.88361416849065e-03 3.08017262426396e-02 - 1.18176401547236e-02 3.37150697939048e-02 - 1.39661993216829e-02 3.66903720067988e-02 - 1.62951420791042e-02 3.96771612113458e-02 - 1.88631937781153e-02 4.27454120317739e-02 - 2.16807137532775e-02 4.58725042740357e-02 - 2.47159162958630e-02 4.90115422967287e-02 - 2.80064400105862e-02 5.21750894902823e-02 - 3.15762558914965e-02 5.54505014956785e-02 - 3.53948396168776e-02 5.88185867162710e-02 - 3.94949825480075e-02 6.22225623243148e-02 - 4.38979282781582e-02 6.56555400487561e-02 - 4.85758075737765e-02 6.90684174618877e-02 - 5.35679916138119e-02 7.24986074502804e-02 - 5.88818211488708e-02 7.59324117267348e-02 - 6.45001629027312e-02 7.93521595635579e-02 - 7.04692046391145e-02 8.27727241953833e-02 - 7.67740309924711e-02 8.61656048178345e-02 - 8.34162127168367e-02 8.95293142943244e-02 - 9.04290195190654e-02 9.28522668276151e-02 - 9.77906533229447e-02 9.61258956464518e-02 - 1.05536187198748e-01 9.93339293936663e-02 - 1.13658760041779e-01 1.02465212366664e-01 - 1.22161483318940e-01 1.05511491883248e-01 - 1.31067498602735e-01 1.08459730671467e-01 - 1.40354649921884e-01 1.11286188625079e-01 - 1.50055110786138e-01 1.13987675746046e-01 - 1.60148962661562e-01 1.16529466367561e-01 - 1.70658187899640e-01 1.18920925097680e-01 - 1.81574957422924e-01 1.21135256056331e-01 - 1.92907571409635e-01 1.23162443963405e-01 - 2.04657634577812e-01 1.24979065894255e-01 - 2.16817353069425e-01 1.26576149394457e-01 - 2.29396483963478e-01 1.27949184305729e-01 - 2.42377800694080e-01 1.29095326655683e-01 - 2.55773624268338e-01 1.29996244273358e-01 - 2.69566785632899e-01 1.30642288615384e-01 - 2.83765797226135e-01 1.31021147084469e-01 - 2.98347982887804e-01 1.31121715408411e-01 - 3.13318978785268e-01 1.30955743796645e-01 - 3.28658461892810e-01 1.30510745398534e-01 - 3.44364941645546e-01 1.29797206143129e-01 - 3.60419773725681e-01 1.28798956699326e-01 - 3.76811233766957e-01 1.27542513884833e-01 - 3.93525251020729e-01 1.26022773725181e-01 - 4.10538642553571e-01 1.24256854102625e-01 - 4.27843232490823e-01 1.22232587821258e-01 - 4.45406663468198e-01 1.19973198285664e-01 - 4.63222254103030e-01 1.17486512685501e-01 - 4.81251545655716e-01 1.14780863513545e-01 - 4.99481026671737e-01 1.11865533884454e-01 - 5.17879583085697e-01 1.08760299105465e-01 - 5.36417631367010e-01 1.05490613602992e-01 - 5.55075704909560e-01 1.02058021605140e-01 - 5.73808427242608e-01 9.84827599501655e-02 - 5.92596731105059e-01 9.47854570249413e-02 - 6.11401377553511e-01 9.09733652959178e-02 - 6.30186430605241e-01 8.70662928751057e-02 - 6.48926781663159e-01 8.30878278025372e-02 - 6.67570206424973e-01 7.90600015070046e-02 - 6.86088429590952e-01 7.50071806168531e-02 - 7.04445389043917e-01 7.09399724049648e-02 - 7.22592093722966e-01 6.68804147042393e-02 - 7.40501800453524e-01 6.28466724805442e-02 - 7.58125457122835e-01 5.88643138494655e-02 - 7.75421014376153e-01 5.49443532270409e-02 - 7.92362373587600e-01 5.11080009416383e-02 - 8.08894546151696e-01 4.73634027837852e-02 - 8.24974633014891e-01 4.37352519908039e-02 - 8.40576952273409e-01 4.02314624594199e-02 - 8.55652758808818e-01 3.68552089767892e-02 - 8.70162898882712e-01 3.36249366753528e-02 - 8.84085033071272e-01 3.05494275915640e-02 - 8.97361214262371e-01 2.76383657210916e-02 - 9.09954680076662e-01 2.48951185873693e-02 - 9.21851471402547e-01 2.23202922175006e-02 - 9.33012836658427e-01 1.99303268583859e-02 - 9.43389278969050e-01 1.77264265125382e-02 - 9.52973153850560e-01 1.56997870881073e-02 - 9.61743130827061e-01 1.38447097736120e-02 - 9.69640690675464e-01 1.21683419192162e-02 - 9.76664215898664e-01 1.06781170435629e-02 - 9.82815077112014e-01 9.37423985963638e-03 - 9.88028440045103e-01 8.26434837733416e-03 - 9.92304836603751e-01 7.35276245082877e-03 - 9.95693518775914e-01 6.63111264706433e-03 - 9.98120489340015e-01 6.12182772221236e-03 - 9.99443037908705e-01 5.83962490929096e-03 - 1.00000000000000e+00 5.71916428310916e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_29.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_29.dat index 6dcc6557..57abe49a 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_29.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_29.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_29_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF29_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF29_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.844986 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.390199 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.707542 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.018568 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.840677 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.031777 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006858 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085783 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.008960 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085728 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -3.12773544964694e-03 1.22752995201793e-02 4.91634654516457e-03 --1.77714285740401e+02 6.47990994194543e-02 1.58592766452930e-02 9.15344357415297e-02 --1.75428571400002e+02 1.30287241837884e-01 1.57616548060771e-02 1.82529284872279e-01 --1.73142857116900e+02 1.87562567920466e-01 1.57885389531763e-02 2.74877385315523e-01 --1.70857160423602e+02 2.40169824223674e-01 2.06498138507955e-02 3.65059775065759e-01 --1.68571631778825e+02 2.91454042997423e-01 3.40199582125212e-02 3.97230647971176e-01 --1.66285714267592e+02 3.44520503119631e-01 5.55034257944890e-02 3.92287851521474e-01 --1.63999999984490e+02 4.02450579267227e-01 8.36815471043075e-02 3.86572188568623e-01 --1.61714472886699e+02 4.68421931478298e-01 1.16710290127135e-01 3.82505889023776e-01 --1.59428371284127e+02 5.43741828205567e-01 1.53643207559961e-01 3.82904262455526e-01 --1.57142842639350e+02 6.21291467543920e-01 1.94171577794414e-01 4.00053854114020e-01 --1.54857313994574e+02 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0.00000000000000e+00 1.27312001091097e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_29_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_29_Coords.txt deleted file mode 100644 index 157a3286..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_29_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.288759 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -4.28407838448215e-03 - 9.99429683992583e-01 -4.19326633040914e-03 - 9.98063017832965e-01 -3.97695915953284e-03 - 9.95573914266674e-01 -3.58771398059781e-03 - 9.92086309749559e-01 -3.05237888133008e-03 - 9.87686148675057e-01 -2.39158858235296e-03 - 9.82330525170640e-01 -1.61725225144229e-03 - 9.76011908335692e-01 -7.52328601041652e-04 - 9.68787467298381e-01 1.70013159228444e-04 - 9.60674860259240e-01 1.12205924749463e-03 - 9.51675358763677e-01 2.07177047610264e-03 - 9.41827652746244e-01 2.99157724731896e-03 - 9.31175295355131e-01 3.79564373614779e-03 - 9.19730397431178e-01 4.44175476053957e-03 - 9.07524559194720e-01 4.85532571839932e-03 - 8.94610408070308e-01 4.97255340617705e-03 - 8.81009696499435e-01 4.76209576634707e-03 - 8.66747905197194e-01 4.16570974637450e-03 - 8.51890258171205e-01 3.19589838023829e-03 - 8.36469462621421e-01 1.81110669892603e-03 - 8.20513485943698e-01 -1.84209354088586e-05 - 8.04073832217581e-01 -2.32561267082903e-03 - 7.87191529885653e-01 -5.17710434961832e-03 - 7.69897919101553e-01 -8.61611650590870e-03 - 7.52252341235159e-01 -1.26353578505725e-02 - 7.34291349178558e-01 -1.72014914970386e-02 - 7.16044924955764e-01 -2.22560348108661e-02 - 6.97571640033109e-01 -2.77520655730733e-02 - 6.78906186433687e-01 -3.36489704426518e-02 - 6.60080312620540e-01 -3.98737091456076e-02 - 6.41147517137212e-01 -4.63411119089972e-02 - 6.22137650968852e-01 -5.29538991170928e-02 - 6.03087998194415e-01 -5.96076177780200e-02 - 5.84045042118975e-01 -6.62201108356666e-02 - 5.65030897687003e-01 -7.26920504436682e-02 - 5.46088602779599e-01 -7.89441574029267e-02 - 5.27248673916899e-01 -8.49088648928683e-02 - 5.08535950506088e-01 -9.05239654188862e-02 - 4.89992355470388e-01 -9.57427025889960e-02 - 4.71632114506831e-01 -1.00519410709185e-01 - 4.53492503744347e-01 -1.04828412465697e-01 - 4.35593302897673e-01 -1.08653064286015e-01 - 4.17956065616942e-01 -1.12005894801822e-01 - 4.00609748442576e-01 -1.14884241730672e-01 - 3.83560931606009e-01 -1.17303456035053e-01 - 3.66843215733716e-01 -1.19263006941430e-01 - 3.50457316320503e-01 -1.20780507098589e-01 - 3.34434484008630e-01 -1.21877989029133e-01 - 3.18774100329315e-01 -1.22583106302361e-01 - 3.03499623121295e-01 -1.22892852070706e-01 - 2.88611293565648e-01 -1.22857057320315e-01 - 2.74124386665666e-01 -1.22464884546138e-01 - 2.60041455523719e-01 -1.21763967760911e-01 - 2.46374872015917e-01 -1.20756391833616e-01 - 2.33123443938834e-01 -1.19478013741279e-01 - 2.20293777810423e-01 -1.17935112270143e-01 - 2.07883282965331e-01 -1.16143383793851e-01 - 1.95902956391646e-01 -1.14131648607952e-01 - 1.84341253066628e-01 -1.11899966738832e-01 - 1.73213930954160e-01 -1.09486519389225e-01 - 1.62499176129638e-01 -1.06894660508144e-01 - 1.52214602777260e-01 -1.04155126826506e-01 - 1.42331759398971e-01 -1.01276909564164e-01 - 1.32872111539190e-01 -9.82863244981183e-02 - 1.23806439629760e-01 -9.51950942807024e-02 - 1.15147623386077e-01 -9.20155582703246e-02 - 1.06887208802748e-01 -8.87757618460561e-02 - 9.90071115215634e-02 -8.54774383402142e-02 - 9.15234043853439e-02 -8.21581150316781e-02 - 8.43970428172224e-02 -7.88082088515410e-02 - 7.76464790199521e-02 -7.54532788193476e-02 - 7.12479082120209e-02 -7.20977713581526e-02 - 6.51878662973747e-02 -6.87515983615688e-02 - 5.94874721274202e-02 -6.54304022859492e-02 - 5.41002464180900e-02 -6.21339535526754e-02 - 4.90378786701877e-02 -5.88934949671291e-02 - 4.43003497573338e-02 -5.57327334902874e-02 - 3.98423597346806e-02 -5.26150738134350e-02 - 3.56899752436130e-02 -4.95627042555296e-02 - 3.18292350050658e-02 -4.65806872714300e-02 - 2.82200072057899e-02 -4.36377743090267e-02 - 2.48925247792699e-02 -4.07816927771986e-02 - 2.18286683030034e-02 -3.79935824106078e-02 - 1.89846947131331e-02 -3.52658405256147e-02 - 1.63921917020335e-02 -3.26377494438330e-02 - 1.40446346341990e-02 -3.00845132316806e-02 - 1.18798249846349e-02 -2.75410974715806e-02 - 9.93094518736223e-03 -2.50703651572185e-02 - 8.21940795734749e-03 -2.26864370417386e-02 - 6.65838622137879e-03 -2.02978347907637e-02 - 5.26774192850643e-03 -1.81551840868098e-02 - 4.09515753852961e-03 -1.61310555216585e-02 - 3.09878859713640e-03 -1.40812912970634e-02 - 2.19660773551101e-03 -1.19062196239147e-02 - 1.46264176301869e-03 -9.47866413677746e-03 - 9.64484608297914e-04 -6.99606932015201e-03 - 5.99373867982851e-04 -4.68529498057288e-03 - 2.90086645599082e-04 -2.34134254701820e-03 - 7.80707788302466e-05 -6.45879934806277e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 6.53795583666477e-04 - 2.89878724192004e-04 2.80605432785994e-03 - 5.98775316682048e-04 5.90398583000895e-03 - 9.63326351634835e-04 8.62973104615211e-03 - 1.45966821282819e-03 1.14220956432944e-02 - 2.19097636449990e-03 1.40997226340466e-02 - 3.08997841959778e-03 1.68633374555817e-02 - 4.08271112470316e-03 1.93498832591143e-02 - 5.24853124383664e-03 2.19195741241484e-02 - 6.63128223001261e-03 2.46879311177444e-02 - 8.18368429859057e-03 2.73917671347008e-02 - 9.88361416849065e-03 3.00822444355933e-02 - 1.18176401547236e-02 3.29469181721594e-02 - 1.39661993216829e-02 3.58686739687114e-02 - 1.62951420791042e-02 3.87983178376753e-02 - 1.88631937781153e-02 4.18172339805593e-02 - 2.16807137532775e-02 4.48949712873368e-02 - 2.47159162958630e-02 4.79862186493693e-02 - 2.80064400105862e-02 5.11050040336456e-02 - 3.15762558914965e-02 5.43102051900192e-02 - 3.53948396168776e-02 5.75860027609883e-02 - 3.94949825480075e-02 6.08970489663807e-02 - 4.38979282781582e-02 6.42421048404069e-02 - 4.85758075737765e-02 6.75764590425572e-02 - 5.35679916138119e-02 7.09287210378174e-02 - 5.88818211488708e-02 7.42885148842847e-02 - 6.45001629027312e-02 7.76401306411453e-02 - 7.04692046391145e-02 8.09946321259863e-02 - 7.67740309924711e-02 8.43260152577684e-02 - 8.34162127168367e-02 8.76291793279204e-02 - 9.04290195190654e-02 9.08990073733131e-02 - 9.77906533229447e-02 9.41202760991221e-02 - 1.05536187198748e-01 9.72819662515041e-02 - 1.13658760041779e-01 1.00370724505034e-01 - 1.22161483318940e-01 1.03379121651085e-01 - 1.31067498602735e-01 1.06296338078876e-01 - 1.40354649921884e-01 1.09098376520961e-01 - 1.50055110786138e-01 1.11776245290247e-01 - 1.60148962661562e-01 1.14303753123405e-01 - 1.70658187899640e-01 1.16690298780888e-01 - 1.81574957422924e-01 1.18902034670956e-01 - 1.92907571409635e-01 1.20932138362540e-01 - 2.04657634577812e-01 1.22759726130690e-01 - 2.16817353069425e-01 1.24373855212877e-01 - 2.29396483963478e-01 1.25767393298500e-01 - 2.42377800694080e-01 1.26935649613551e-01 - 2.55773624268338e-01 1.27863776880976e-01 - 2.69566785632899e-01 1.28542667017364e-01 - 2.83765797226135e-01 1.28948609667166e-01 - 2.98347982887804e-01 1.29079109224687e-01 - 3.13318978785268e-01 1.28946301516400e-01 - 3.28658461892810e-01 1.28524042633685e-01 - 3.44364941645546e-01 1.27840398820390e-01 - 3.60419773725681e-01 1.26869307354302e-01 - 3.76811233766957e-01 1.25638663521008e-01 - 3.93525251020729e-01 1.24143985884766e-01 - 4.10538642553571e-01 1.22405375885196e-01 - 4.27843232490823e-01 1.20406764229010e-01 - 4.45406663468198e-01 1.18175535003347e-01 - 4.63222254103030e-01 1.15713874851602e-01 - 4.81251545655716e-01 1.13039416210673e-01 - 4.99481026671737e-01 1.10149207312083e-01 - 5.17879583085697e-01 1.07071518925045e-01 - 5.36417631367010e-01 1.03828127129228e-01 - 5.55075704909560e-01 1.00424069146643e-01 - 5.73808427242608e-01 9.68747553745350e-02 - 5.92596731105059e-01 9.32009355364200e-02 - 6.11401377553511e-01 8.94158298771435e-02 - 6.30186430605241e-01 8.55340315560204e-02 - 6.48926781663159e-01 8.15839888739276e-02 - 6.67570206424973e-01 7.75845254869556e-02 - 6.86088429590952e-01 7.35622927759778e-02 - 7.04445389043917e-01 6.95327571885118e-02 - 7.22592093722966e-01 6.55115439825422e-02 - 7.40501800453524e-01 6.15162401900316e-02 - 7.58125457122835e-01 5.75783230287885e-02 - 7.75421014376153e-01 5.37064454056262e-02 - 7.92362373587600e-01 4.99183683407041e-02 - 8.08894546151696e-01 4.62250537866291e-02 - 8.24974633014891e-01 4.26511530337529e-02 - 8.40576952273409e-01 3.91976188659757e-02 - 8.55652758808818e-01 3.58748347811836e-02 - 8.70162898882712e-01 3.26960061377798e-02 - 8.84085033071272e-01 2.96677876923448e-02 - 8.97361214262371e-01 2.68060209254739e-02 - 9.09954680076662e-01 2.41045019761916e-02 - 9.21851471402547e-01 2.15734841233251e-02 - 9.33012836658427e-01 1.92188847572111e-02 - 9.43389278969050e-01 1.70483619057286e-02 - 9.52973153850560e-01 1.50493850653991e-02 - 9.61743130827061e-01 1.32199413826276e-02 - 9.69640690675464e-01 1.15690089094319e-02 - 9.76664215898664e-01 1.01012469839841e-02 - 9.82815077112014e-01 8.81664542039199e-03 - 9.88028440045103e-01 7.72497700105789e-03 - 9.92304836603751e-01 6.82882364508767e-03 - 9.95693518775914e-01 6.11914324927029e-03 - 9.98120489340015e-01 5.61563152039012e-03 - 9.99443037908705e-01 5.33830998610357e-03 - 1.00000000000000e+00 5.22050363236317e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_30.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_30.dat index 976f2fd9..cc68f636 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_30.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_30.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_30_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF30_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF30_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.841912 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.335409 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.721656 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.010919 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.841524 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.022323 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006692 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085742 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.008615 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085620 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 3.82933937602250e-03 1.18847894273075e-02 4.91853635359245e-03 --1.77714285740401e+02 6.34867948330112e-02 1.54143666871474e-02 9.15423409473158e-02 --1.75428571400002e+02 1.27668691191179e-01 1.52977872137544e-02 1.82501714703118e-01 --1.73142857116900e+02 1.84415779953887e-01 1.52422633942091e-02 2.74940119789790e-01 --1.70857160423602e+02 2.36810254422080e-01 2.00498049812939e-02 3.64966832722254e-01 --1.68571631778825e+02 2.87872198391803e-01 3.34779913921736e-02 3.96641245996494e-01 --1.66285714267592e+02 3.40560958108825e-01 5.51365536293886e-02 3.90704398170445e-01 --1.63999999984490e+02 3.97811909899093e-01 8.35891256140358e-02 3.83664147211327e-01 --1.61714472886699e+02 4.62597567662095e-01 1.17044053328997e-01 3.78912395963907e-01 --1.59428371284127e+02 5.36020846864223e-01 1.54493122472992e-01 3.78368767885690e-01 --1.57142842639350e+02 6.11318489334495e-01 1.95588111714744e-01 3.95591242268052e-01 --1.54857313994574e+02 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0.00000000000000e+00 1.20832240887503e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_30_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_30_Coords.txt deleted file mode 100644 index adaa360d..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_30_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.289913 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.76594103107672e-03 - 9.99429683992583e-01 -3.67573296034448e-03 - 9.98063017832965e-01 -3.46125169506945e-03 - 9.95573914266674e-01 -3.07671200357177e-03 - 9.92086309749559e-01 -2.55097030785410e-03 - 9.87686148675057e-01 -1.90838607718942e-03 - 9.82330525170640e-01 -1.15975422803973e-03 - 9.76011908335692e-01 -3.24915605469972e-04 - 9.68787467298381e-01 5.66663276021817e-04 - 9.60674860259240e-01 1.49117195072950e-03 - 9.51675358763677e-01 2.42528214135727e-03 - 9.41827652746244e-01 3.34619033429496e-03 - 9.31175295355131e-01 4.15486648669930e-03 - 9.19730397431178e-01 4.81000854528531e-03 - 9.07524559194720e-01 5.24466413080883e-03 - 8.94610408070308e-01 5.38441859273748e-03 - 8.81009696499435e-01 5.21317476074425e-03 - 8.66747905197194e-01 4.66703672698767e-03 - 8.51890258171205e-01 3.76187334419197e-03 - 8.36469462621421e-01 2.45499526645557e-03 - 8.20513485943698e-01 7.14407876190322e-04 - 8.04073832217581e-01 -1.48859473539800e-03 - 7.87191529885653e-01 -4.22276309501669e-03 - 7.69897919101553e-01 -7.52905548730649e-03 - 7.52252341235159e-01 -1.14011369654495e-02 - 7.34291349178558e-01 -1.58140642608251e-02 - 7.16044924955764e-01 -2.07082438318535e-02 - 6.97571640033109e-01 -2.60405567076506e-02 - 6.78906186433687e-01 -3.17725916318670e-02 - 6.60080312620540e-01 -3.78335251294081e-02 - 6.41147517137212e-01 -4.41395255179577e-02 - 6.22137650968852e-01 -5.05960415507183e-02 - 6.03087998194415e-01 -5.71012097717806e-02 - 5.84045042118975e-01 -6.35728414924128e-02 - 5.65030897687003e-01 -6.99161725398384e-02 - 5.46088602779599e-01 -7.60508884587764e-02 - 5.27248673916899e-01 -8.19092759841170e-02 - 5.08535950506088e-01 -8.74256140721241e-02 - 4.89992355470388e-01 -9.25608801379942e-02 - 4.71632114506831e-01 -9.72602459916977e-02 - 4.53492503744347e-01 -1.01494058807882e-01 - 4.35593302897673e-01 -1.05246180821216e-01 - 4.17956065616942e-01 -1.08533395639028e-01 - 4.00609748442576e-01 -1.11343147013635e-01 - 3.83560931606009e-01 -1.13704864927681e-01 - 3.66843215733716e-01 -1.15609362965306e-01 - 3.50457316320503e-01 -1.17077806029666e-01 - 3.34434484008630e-01 -1.18131610569872e-01 - 3.18774100329315e-01 -1.18799489327838e-01 - 3.03499623121295e-01 -1.19079080276086e-01 - 2.88611293565648e-01 -1.19021671063012e-01 - 2.74124386665666e-01 -1.18610811385520e-01 - 2.60041455523719e-01 -1.17903459093290e-01 - 2.46374872015917e-01 -1.16897095674562e-01 - 2.33123443938834e-01 -1.15627576280488e-01 - 2.20293777810423e-01 -1.14105943915663e-01 - 2.07883282965331e-01 -1.12339501922782e-01 - 1.95902956391646e-01 -1.10364799915455e-01 - 1.84341253066628e-01 -1.08178194919267e-01 - 1.73213930954160e-01 -1.05820879232865e-01 - 1.62499176129638e-01 -1.03292498069936e-01 - 1.52214602777260e-01 -1.00622744494138e-01 - 1.42331759398971e-01 -9.78213431038057e-02 - 1.32872111539190e-01 -9.49182293217050e-02 - 1.23806439629760e-01 -9.19184438504510e-02 - 1.15147623386077e-01 -8.88378169959806e-02 - 1.06887208802748e-01 -8.57023303938976e-02 - 9.90071115215634e-02 -8.25118222667112e-02 - 9.15234043853439e-02 -7.93018807409516e-02 - 8.43970428172224e-02 -7.60695660391565e-02 - 7.76464790199521e-02 -7.28312494732273e-02 - 7.12479082120209e-02 -6.95988911505855e-02 - 6.51878662973747e-02 -6.63772605194339e-02 - 5.94874721274202e-02 -6.31823261707942e-02 - 5.41002464180900e-02 -6.00148738797130e-02 - 4.90378786701877e-02 -5.69004008313318e-02 - 4.43003497573338e-02 -5.38517567259466e-02 - 3.98423597346806e-02 -5.08444825528229e-02 - 3.56899752436130e-02 -4.78999246744473e-02 - 3.18292350050658e-02 -4.50242634039351e-02 - 2.82200072057899e-02 -4.21866345165205e-02 - 2.48925247792699e-02 -3.94345087948828e-02 - 2.18286683030034e-02 -3.67496113164531e-02 - 1.89846947131331e-02 -3.41270218043207e-02 - 1.63921917020335e-02 -3.16012998390213e-02 - 1.40446346341990e-02 -2.91333141116453e-02 - 1.18798249846349e-02 -2.66809583438181e-02 - 9.93094518736223e-03 -2.43050742807526e-02 - 8.21940795734749e-03 -2.20089879479418e-02 - 6.65838622137879e-03 -1.97051139981199e-02 - 5.26774192850643e-03 -1.76775332774475e-02 - 4.09515753852961e-03 -1.57641171424597e-02 - 3.09878859713640e-03 -1.37808713395637e-02 - 2.19660773551101e-03 -1.15906992105468e-02 - 1.46264176301869e-03 -9.10546062500458e-03 - 9.64484608297914e-04 -6.49590167899531e-03 - 5.99373867982851e-04 -4.19239728064800e-03 - 2.90086645599082e-04 -2.04986425772061e-03 - 7.80707788302466e-05 -5.54189387781071e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 5.63185471180581e-04 - 2.89878724192004e-04 2.34042919757741e-03 - 5.98775316682048e-04 5.09573827078158e-03 - 9.63326351634835e-04 8.00115783273371e-03 - 1.45966821282819e-03 1.09544529452719e-02 - 2.19097636449990e-03 1.36866128445040e-02 - 3.08997841959778e-03 1.64105857390048e-02 - 4.08271112470316e-03 1.88290076612881e-02 - 5.24853124383664e-03 2.13445652338093e-02 - 6.63128223001261e-03 2.40683661044272e-02 - 8.18368429859057e-03 2.67264136294098e-02 - 9.88361416849065e-03 2.93576735827575e-02 - 1.18176401547236e-02 3.21727740884816e-02 - 1.39661993216829e-02 3.50414045343185e-02 - 1.62951420791042e-02 3.79153767236490e-02 - 1.88631937781153e-02 4.08849588626939e-02 - 2.16807137532775e-02 4.39138240893539e-02 - 2.47159162958630e-02 4.69579389809846e-02 - 2.80064400105862e-02 5.00327922947516e-02 - 3.15762558914965e-02 5.31717703575268e-02 - 3.53948396168776e-02 5.63614479218556e-02 - 3.94949825480075e-02 5.95864374425640e-02 - 4.38979282781582e-02 6.28503520802363e-02 - 4.85758075737765e-02 6.61125308808324e-02 - 5.35679916138119e-02 6.93936319764484e-02 - 5.88818211488708e-02 7.26864745071358e-02 - 6.45001629027312e-02 7.59767143061168e-02 - 7.04692046391145e-02 7.92722686337076e-02 - 7.67740309924711e-02 8.25493054410369e-02 - 8.34162127168367e-02 8.57995017186479e-02 - 9.04290195190654e-02 8.90233332913648e-02 - 9.77906533229447e-02 9.21997393132203e-02 - 1.05536187198748e-01 9.53228649052204e-02 - 1.13658760041779e-01 9.83774858926284e-02 - 1.22161483318940e-01 1.01356111083286e-01 - 1.31067498602735e-01 1.04250057268142e-01 - 1.40354649921884e-01 1.07034682148747e-01 - 1.50055110786138e-01 1.09697598629454e-01 - 1.60148962661562e-01 1.12220196852737e-01 - 1.70658187899640e-01 1.14607444588381e-01 - 1.81574957422924e-01 1.16825619157746e-01 - 1.92907571409635e-01 1.18866841336207e-01 - 2.04657634577812e-01 1.20712555517322e-01 - 2.16817353069425e-01 1.22350714875085e-01 - 2.29396483963478e-01 1.23773693525801e-01 - 2.42377800694080e-01 1.24971127880256e-01 - 2.55773624268338e-01 1.25930912579736e-01 - 2.69566785632899e-01 1.26645340169403e-01 - 2.83765797226135e-01 1.27082774706623e-01 - 2.98347982887804e-01 1.27248420245732e-01 - 3.13318978785268e-01 1.27147985242432e-01 - 3.28658461892810e-01 1.26751033872467e-01 - 3.44364941645546e-01 1.26093408159434e-01 - 3.60419773725681e-01 1.25147365979887e-01 - 3.76811233766957e-01 1.23938482228900e-01 - 3.93525251020729e-01 1.22463388497873e-01 - 4.10538642553571e-01 1.20744123782386e-01 - 4.27843232490823e-01 1.18765881585222e-01 - 4.45406663468198e-01 1.16553168271900e-01 - 4.63222254103030e-01 1.14109063119083e-01 - 4.81251545655716e-01 1.11454214492994e-01 - 4.99481026671737e-01 1.08579965851754e-01 - 5.17879583085697e-01 1.05522245676892e-01 - 5.36417631367010e-01 1.02295810770964e-01 - 5.55075704909560e-01 9.89109539219609e-02 - 5.73808427242608e-01 9.53792812929814e-02 - 5.92596731105059e-01 9.17207717467103e-02 - 6.11401377553511e-01 8.79539813310119e-02 - 6.30186430605241e-01 8.40885118612627e-02 - 6.48926781663159e-01 8.01587183015492e-02 - 6.67570206424973e-01 7.61796953916419e-02 - 6.86088429590952e-01 7.21807683420921e-02 - 7.04445389043917e-01 6.81802889819599e-02 - 7.22592093722966e-01 6.41904749035804e-02 - 7.40501800453524e-01 6.02267264683595e-02 - 7.58125457122835e-01 5.63264715322824e-02 - 7.75421014376153e-01 5.24963888188260e-02 - 7.92362373587600e-01 4.87510494275386e-02 - 8.08894546151696e-01 4.51040136665705e-02 - 8.24974633014891e-01 4.15795961220347e-02 - 8.40576952273409e-01 3.81727689094657e-02 - 8.55652758808818e-01 3.48998191543661e-02 - 8.70162898882712e-01 3.17691564867249e-02 - 8.84085033071272e-01 2.87862841222289e-02 - 8.97361214262371e-01 2.59714142005909e-02 - 9.09954680076662e-01 2.33107232487436e-02 - 9.21851471402547e-01 2.08223116630006e-02 - 9.33012836658427e-01 1.85030698214206e-02 - 9.43389278969050e-01 1.63658828185647e-02 - 9.52973153850560e-01 1.43956137772614e-02 - 9.61743130827061e-01 1.25929982737422e-02 - 9.69640690675464e-01 1.09686747099717e-02 - 9.76664215898664e-01 9.52468308966877e-03 - 9.82815077112014e-01 8.26075843974538e-03 - 9.88028440045103e-01 7.18854428750788e-03 - 9.92304836603751e-01 6.30893418596833e-03 - 9.95693518775914e-01 5.61222040025814e-03 - 9.98120489340015e-01 5.11477961825530e-03 - 9.99443037908705e-01 4.84282690364284e-03 - 1.00000000000000e+00 4.72798936785863e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_31.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_31.dat index dab3908b..834f5fae 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_31.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_31.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_31_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF31_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF31_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.844554 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.346612 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.727018 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.007935 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.841558 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.046097 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006609 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085546 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.008308 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085502 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 6.47227103185885e-03 1.17532602015116e-02 4.91936366501836e-03 --1.77714285740401e+02 6.24374112692928e-02 1.52637743340200e-02 9.15453440656006e-02 --1.75428571400002e+02 1.25576445571001e-01 1.51403857201786e-02 1.82491241037869e-01 --1.73142857116900e+02 1.81740229532184e-01 1.50549486908293e-02 2.74963952065870e-01 --1.70857160423602e+02 2.33761281328417e-01 1.98418703753333e-02 3.64931524741820e-01 --1.68571631778825e+02 2.84469149422810e-01 3.32888447164394e-02 3.96059360581104e-01 --1.66285714267592e+02 3.36709170965683e-01 5.50079908384307e-02 3.89157116793139e-01 --1.63999999984490e+02 3.93301041770278e-01 8.35568398800086e-02 3.81010907259297e-01 --1.61714472886699e+02 4.57076609698803e-01 1.17496232230119e-01 3.75436178372868e-01 --1.59428371284127e+02 5.29033696059146e-01 1.55588854185241e-01 3.74082261913029e-01 --1.57142842639350e+02 6.02679383011616e-01 1.97318066010756e-01 3.91326773326504e-01 --1.54857313994574e+02 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0.00000000000000e+00 1.17895309867403e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_31_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_31_Coords.txt deleted file mode 100644 index af64aa94..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_31_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.291568 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.26000000000000e-03 - 9.99429683992583e-01 -3.17197061384716e-03 - 9.98063017832965e-01 -2.96292967126308e-03 - 9.95573914266674e-01 -2.58907063225710e-03 - 9.92086309749559e-01 -2.07988996410121e-03 - 9.87686148675057e-01 -1.46130981799122e-03 - 9.82330525170640e-01 -7.43109370372039e-04 - 9.76011908335692e-01 5.71802038815845e-05 - 9.68787467298381e-01 9.12850307932250e-04 - 9.60674860259240e-01 1.80269997277206e-03 - 9.51675358763677e-01 2.70812011853604e-03 - 9.41827652746244e-01 3.60866977394845e-03 - 9.31175295355131e-01 4.40395029836166e-03 - 9.19730397431178e-01 5.04714011154833e-03 - 9.07524559194720e-01 5.47727001358693e-03 - 8.94610408070308e-01 5.61958000000000e-03 - 8.81009696499435e-01 5.46534993988919e-03 - 8.66747905197194e-01 4.95248978743049e-03 - 8.51890258171205e-01 4.09406987682545e-03 - 8.36469462621421e-01 2.84598023891681e-03 - 8.20513485943698e-01 1.17918953274594e-03 - 8.04073832217581e-01 -9.33739688073435e-04 - 7.87191529885653e-01 -3.55842001924847e-03 - 7.69897919101553e-01 -6.73447017631892e-03 - 7.52252341235159e-01 -1.04541897247412e-02 - 7.34291349178558e-01 -1.47010702029328e-02 - 7.16044924955764e-01 -1.94213586696945e-02 - 6.97571640033109e-01 -2.45750799904683e-02 - 6.78906186433687e-01 -3.01265610867414e-02 - 6.60080312620540e-01 -3.60081091667057e-02 - 6.41147517137212e-01 -4.21379109367429e-02 - 6.22137650968852e-01 -4.84252296784254e-02 - 6.03087998194415e-01 -5.47705806004636e-02 - 5.84045042118975e-01 -6.10933093024556e-02 - 5.65030897687003e-01 -6.72996007442982e-02 - 5.46088602779599e-01 -7.33101691354299e-02 - 5.27248673916899e-01 -7.90568488365953e-02 - 5.08535950506088e-01 -8.44731198580007e-02 - 4.89992355470388e-01 -8.95220211844568e-02 - 4.71632114506831e-01 -9.41408089191935e-02 - 4.53492503744347e-01 -9.82975991887994e-02 - 4.35593302897673e-01 -1.01975529440012e-01 - 4.17956065616942e-01 -1.05193480742005e-01 - 4.00609748442576e-01 -1.07933450226618e-01 - 3.83560931606009e-01 -1.10233929804933e-01 - 3.66843215733716e-01 -1.12081210413681e-01 - 3.50457316320503e-01 -1.13497740267797e-01 - 3.34434484008630e-01 -1.14505719803901e-01 - 3.18774100329315e-01 -1.15133309992439e-01 - 3.03499623121295e-01 -1.15379680000000e-01 - 2.88611293565648e-01 -1.15297210033408e-01 - 2.74124386665666e-01 -1.14866039874578e-01 - 2.60041455523719e-01 -1.14148859730103e-01 - 2.46374872015917e-01 -1.13141310167743e-01 - 2.33123443938834e-01 -1.11877760414519e-01 - 2.20293777810423e-01 -1.10373249720014e-01 - 2.07883282965331e-01 -1.08630430446335e-01 - 1.95902956391646e-01 -1.06689389375606e-01 - 1.84341253066628e-01 -1.04544540600570e-01 - 1.73213930954160e-01 -1.02238620208274e-01 - 1.62499176129638e-01 -9.97698090659131e-02 - 1.52214602777260e-01 -9.71658307337490e-02 - 1.42331759398971e-01 -9.44377698276564e-02 - 1.32872111539190e-01 -9.16174204761496e-02 - 1.23806439629760e-01 -8.87050298768115e-02 - 1.15147623386077e-01 -8.57190212052115e-02 - 1.06887208802748e-01 -8.26828495457969e-02 - 9.90071115215634e-02 -7.95956806133001e-02 - 9.15234043853439e-02 -7.64911518688338e-02 - 8.43970428172224e-02 -7.33704712685308e-02 - 7.76464790199521e-02 -7.02441095346318e-02 - 7.12479082120209e-02 -6.71283691072125e-02 - 6.51878662973747e-02 -6.40249080540733e-02 - 5.94874721274202e-02 -6.09500111747720e-02 - 5.41002464180900e-02 -5.79043079283336e-02 - 4.90378786701877e-02 -5.49088591942904e-02 - 4.43003497573338e-02 -5.19696098458621e-02 - 3.98423597346806e-02 -4.90703398230878e-02 - 3.56899752436130e-02 -4.62315066678512e-02 - 3.18292350050658e-02 -4.34599463166414e-02 - 2.82200072057899e-02 -4.07256778291602e-02 - 2.48925247792699e-02 -3.80747039176243e-02 - 2.18286683030034e-02 -3.54905785323845e-02 - 1.89846947131331e-02 -3.29685742961468e-02 - 1.63921917020335e-02 -3.05397416585206e-02 - 1.40446346341990e-02 -2.81598748717060e-02 - 1.18798249846349e-02 -2.57991456362272e-02 - 9.93094518736223e-03 -2.35141340822677e-02 - 8.21940795734749e-03 -2.13065372406694e-02 - 6.65838622137879e-03 -1.90964147052845e-02 - 5.26774192850643e-03 -1.71669328325963e-02 - 4.09515753852961e-03 -1.53436557497530e-02 - 3.09878859713640e-03 -1.34221169770868e-02 - 2.19660773551101e-03 -1.12291535125844e-02 - 1.46264176301869e-03 -8.70563746430323e-03 - 9.64484608297914e-04 -6.05715634209525e-03 - 5.99373867982851e-04 -3.81824422537424e-03 - 2.90086645599082e-04 -1.84122859342309e-03 - 7.80707788302466e-05 -4.90184920651700e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 5.06578196326823e-04 - 2.89878724192004e-04 2.04452028038426e-03 - 5.98775316682048e-04 4.53717231306803e-03 - 9.63326351634835e-04 7.46212449708706e-03 - 1.45966821282819e-03 1.04985915071135e-02 - 2.19097636449990e-03 1.32707478160275e-02 - 3.08997841959778e-03 1.59509958179301e-02 - 4.08271112470316e-03 1.83045125133814e-02 - 5.24853124383664e-03 2.07610725089213e-02 - 6.63128223001261e-03 2.34294740113542e-02 - 8.18368429859057e-03 2.60379468512300e-02 - 9.88361416849065e-03 2.86109061286680e-02 - 1.18176401547236e-02 3.13718702114807e-02 - 1.39661993216829e-02 3.41846291465346e-02 - 1.62951420791042e-02 3.70023324372690e-02 - 1.88631937781153e-02 3.99191441385704e-02 - 2.16807137532775e-02 4.28962538313677e-02 - 2.47159162958630e-02 4.58905064712631e-02 - 2.80064400105862e-02 4.89184500094274e-02 - 3.15762558914965e-02 5.19955665556731e-02 - 3.53948396168776e-02 5.51094996967499e-02 - 3.94949825480075e-02 5.82601219021923e-02 - 4.38979282781582e-02 6.14539887873536e-02 - 4.85758075737765e-02 6.46534383886963e-02 - 5.35679916138119e-02 6.78734310113314e-02 - 5.88818211488708e-02 7.11095406805867e-02 - 6.45001629027312e-02 7.43478916250517e-02 - 7.04692046391145e-02 7.75944324493063e-02 - 7.67740309924711e-02 8.08267804937443e-02 - 8.34162127168367e-02 8.40345012725877e-02 - 9.04290195190654e-02 8.72217497882376e-02 - 9.77906533229447e-02 9.03635913718733e-02 - 1.05536187198748e-01 9.34585289184932e-02 - 1.13658760041779e-01 9.64904400150551e-02 - 1.22161483318940e-01 9.94503211133352e-02 - 1.31067498602735e-01 1.02331419565693e-01 - 1.40354649921884e-01 1.05107809977648e-01 - 1.50055110786138e-01 1.07767850205960e-01 - 1.60148962661562e-01 1.10298000635614e-01 - 1.70658187899640e-01 1.12692979546625e-01 - 1.81574957422924e-01 1.14929769502905e-01 - 1.92907571409635e-01 1.16993320239739e-01 - 2.04657634577812e-01 1.18866540676069e-01 - 2.16817353069425e-01 1.20537860387127e-01 - 2.29396483963478e-01 1.22002360415503e-01 - 2.42377800694080e-01 1.23238840058052e-01 - 2.55773624268338e-01 1.24236360269181e-01 - 2.69566785632899e-01 1.24989749818415e-01 - 2.83765797226135e-01 1.25465469944336e-01 - 2.98347982887804e-01 1.25673800000000e-01 - 3.13318978785268e-01 1.25605090009328e-01 - 3.28658461892810e-01 1.25238519943160e-01 - 3.44364941645546e-01 1.24602329921847e-01 - 3.60419773725681e-01 1.23679419760925e-01 - 3.76811233766957e-01 1.22488089701048e-01 - 3.93525251020729e-01 1.21026379904569e-01 - 4.10538642553571e-01 1.19317009727894e-01 - 4.27843232490823e-01 1.17353409703050e-01 - 4.45406663468198e-01 1.15147289546016e-01 - 4.63222254103030e-01 1.12712199418876e-01 - 4.81251545655716e-01 1.10062310660303e-01 - 4.99481026671737e-01 1.07193260537088e-01 - 5.17879583085697e-01 1.04146849476826e-01 - 5.36417631367010e-01 1.00926359757649e-01 - 5.55075704909560e-01 9.75491690942573e-02 - 5.73808427242608e-01 9.40253905272124e-02 - 5.92596731105059e-01 9.03729897821859e-02 - 6.11401377553511e-01 8.66140804957621e-02 - 6.30186430605241e-01 8.27543598745400e-02 - 6.48926781663159e-01 7.88349696491208e-02 - 6.67570206424973e-01 7.48670807649720e-02 - 6.86088429590952e-01 7.08832100883683e-02 - 7.04445389043917e-01 6.69008402082011e-02 - 7.22592093722966e-01 6.29341191835659e-02 - 7.40501800453524e-01 5.89939299003046e-02 - 7.58125457122835e-01 5.51229706317405e-02 - 7.75421014376153e-01 5.13266690406267e-02 - 7.92362373587600e-01 4.76171592158252e-02 - 8.08894546151696e-01 4.40098208363926e-02 - 8.24974633014891e-01 4.05285693485989e-02 - 8.40576952273409e-01 3.71641795115098e-02 - 8.55652758808818e-01 3.39361102542322e-02 - 8.70162898882712e-01 3.08491102368075e-02 - 8.84085033071272e-01 2.79092293552106e-02 - 8.97361214262371e-01 2.51378091116254e-02 - 9.09954680076662e-01 2.25170999841380e-02 - 9.21851471402547e-01 2.00692897122379e-02 - 9.33012836658427e-01 1.77856306805394e-02 - 9.43389278969050e-01 1.56818702088261e-02 - 9.52973153850560e-01 1.37423292209950e-02 - 9.61743130827061e-01 1.19686398327912e-02 - 9.69640690675464e-01 1.03725298635384e-02 - 9.76664215898664e-01 8.95410082797074e-03 - 9.82815077112014e-01 7.71282058260575e-03 - 9.88028440045103e-01 6.66145999090718e-03 - 9.92304836603751e-01 5.79959068429709e-03 - 9.95693518775914e-01 5.11699024651898e-03 - 9.98120489340015e-01 4.62832013286718e-03 - 9.99443037908705e-01 4.36210042093713e-03 - 1.00000000000000e+00 4.25000000000000e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_32.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_32.dat index aebb0933..646ab331 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_32.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_32.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_32_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF32_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF32_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.857966 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.444819 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.724134 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.008983 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.839036 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.058412 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006571 Cd0 ! 2D drag coefficient value at 0-lift. - -0.085083 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.008023 Cd0 ! 2D drag coefficient value at 0-lift. +-0.085243 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 6.24642840098168e-03 1.22442836792188e-02 4.91863286417917e-03 --1.77714285740401e+02 6.15681687354890e-02 1.56589314591234e-02 9.15433283602759e-02 --1.75428571400002e+02 1.23845012198683e-01 1.55779778117071e-02 1.82497736455348e-01 --1.73142857116900e+02 1.79359383862646e-01 1.56486091572570e-02 2.74951732622443e-01 --1.70857160423602e+02 2.30859517753453e-01 2.06211507976087e-02 3.64945335971304e-01 --1.68571631778825e+02 2.81088320074285e-01 3.42151237357512e-02 3.95455328763495e-01 --1.66285714267592e+02 3.32800887240806e-01 5.60381669303492e-02 3.87566973417938e-01 --1.63999999984490e+02 3.88724968986050e-01 8.46591845815532e-02 3.78470754544129e-01 --1.61714472886699e+02 4.51601928999678e-01 1.19010723971304e-01 3.71902316178214e-01 --1.59428371284127e+02 5.22401393964607e-01 1.57641669592403e-01 3.69827247407074e-01 --1.57142842639350e+02 5.94836106768854e-01 1.99871661221911e-01 3.87042658990448e-01 --1.54857313994574e+02 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1.23858350061769e-19 1.20735708463146e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_32_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_32_Coords.txt deleted file mode 100644 index 7b12c32e..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_32_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.293425 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -2.75121544644011e-03 - 9.99429683992583e-01 -2.66675703771298e-03 - 9.98063017832965e-01 -2.46633286806743e-03 - 9.95573914266674e-01 -2.10835088076529e-03 - 9.92086309749559e-01 -1.62171952901928e-03 - 9.87686148675057e-01 -1.03217415727397e-03 - 9.82330525170640e-01 -3.48471826754960e-04 - 9.76011908335692e-01 4.13716194251197e-04 - 9.68787467298381e-01 1.22997548096908e-03 - 9.60674860259240e-01 2.08110860848548e-03 - 9.51675358763677e-01 2.95107486651651e-03 - 9.41827652746244e-01 3.82091021122967e-03 - 9.31175295355131e-01 4.59414384298409e-03 - 9.19730397431178e-01 5.21153173474204e-03 - 9.07524559194720e-01 5.62160384087306e-03 - 8.94610408070308e-01 5.75510032893388e-03 - 8.81009696499435e-01 5.60540355708506e-03 - 8.66747905197194e-01 5.11649214479760e-03 - 8.51890258171205e-01 4.29516596583423e-03 - 8.36469462621421e-01 3.09588972287873e-03 - 8.20513485943698e-01 1.49625513028855e-03 - 8.04073832217581e-01 -5.31247406191023e-04 - 7.87191529885653e-01 -3.04763777105271e-03 - 7.69897919101553e-01 -6.09920818596710e-03 - 7.52252341235159e-01 -9.66787919224919e-03 - 7.34291349178558e-01 -1.37442910507571e-02 - 7.16044924955764e-01 -1.82837213244121e-02 - 6.97571640033109e-01 -2.32488422809093e-02 - 6.78906186433687e-01 -2.86071440277508e-02 - 6.60080312620540e-01 -3.42948754293689e-02 - 6.41147517137212e-01 -4.02330445511399e-02 - 6.22137650968852e-01 -4.63359719455746e-02 - 6.03087998194415e-01 -5.25068589555577e-02 - 5.84045042118975e-01 -5.86683304502415e-02 - 5.65030897687003e-01 -6.47247930049999e-02 - 5.46088602779599e-01 -7.06000084115480e-02 - 5.27248673916899e-01 -7.62252542136345e-02 - 5.08535950506088e-01 -8.15358195242986e-02 - 4.89992355470388e-01 -8.64918603226657e-02 - 4.71632114506831e-01 -9.10234712776584e-02 - 4.53492503744347e-01 -9.50980520440851e-02 - 4.35593302897673e-01 -9.86968695822669e-02 - 4.17956065616942e-01 -1.01838974506852e-01 - 4.00609748442576e-01 -1.04504805813471e-01 - 3.83560931606009e-01 -1.06737656852978e-01 - 3.66843215733716e-01 -1.08523025702669e-01 - 3.50457316320503e-01 -1.09882513076487e-01 - 3.34434484008630e-01 -1.10840512299539e-01 - 3.18774100329315e-01 -1.11423001195803e-01 - 3.03499623121295e-01 -1.11631718317104e-01 - 2.88611293565648e-01 -1.11519746655354e-01 - 2.74124386665666e-01 -1.11065860776490e-01 - 2.60041455523719e-01 -1.10335208053040e-01 - 2.46374872015917e-01 -1.09324293348290e-01 - 2.33123443938834e-01 -1.08064368130296e-01 - 2.20293777810423e-01 -1.06573991780711e-01 - 2.07883282965331e-01 -1.04854579703403e-01 - 1.95902956391646e-01 -1.02945815443809e-01 - 1.84341253066628e-01 -1.00841815294268e-01 - 1.73213930954160e-01 -9.85854813152245e-02 - 1.62499176129638e-01 -9.61756468262968e-02 - 1.52214602777260e-01 -9.36370189126117e-02 - 1.42331759398971e-01 -9.09827723769924e-02 - 1.32872111539190e-01 -8.82449252029674e-02 - 1.23806439629760e-01 -8.54204745351098e-02 - 1.15147623386077e-01 -8.25297583092822e-02 - 1.06887208802748e-01 -7.95930660837443e-02 - 9.90071115215634e-02 -7.66100518032005e-02 - 9.15234043853439e-02 -7.36122747240876e-02 - 8.43970428172224e-02 -7.06029385172171e-02 - 7.76464790199521e-02 -6.75894365236451e-02 - 7.12479082120209e-02 -6.45896388237266e-02 - 6.51878662973747e-02 -6.16038487559256e-02 - 5.94874721274202e-02 -5.86486967854928e-02 - 5.41002464180900e-02 -5.57235242625987e-02 - 4.90378786701877e-02 -5.28459400693205e-02 - 4.43003497573338e-02 -5.00183713601190e-02 - 3.98423597346806e-02 -4.72295943403892e-02 - 3.56899752436130e-02 -4.44991118814580e-02 - 3.18292350050658e-02 -4.18340118321882e-02 - 2.82200072057899e-02 -3.92057251006610e-02 - 2.48925247792699e-02 -3.66575570892001e-02 - 2.18286683030034e-02 -3.41761811810127e-02 - 1.89846947131331e-02 -3.17546997715640e-02 - 1.63921917020335e-02 -2.94216357695083e-02 - 1.40446346341990e-02 -2.71361587353816e-02 - 1.18798249846349e-02 -2.48713091371595e-02 - 9.93094518736223e-03 -2.26772082780271e-02 - 8.21940795734749e-03 -2.05622745912398e-02 - 6.65838622137879e-03 -1.84575854051295e-02 - 5.26774192850643e-03 -1.66149163956346e-02 - 4.09515753852961e-03 -1.48646747148321e-02 - 3.09878859713640e-03 -1.30010958813573e-02 - 2.19660773551101e-03 -1.08179372083226e-02 - 1.46264176301869e-03 -8.27283453975058e-03 - 9.64484608297914e-04 -5.65417816593411e-03 - 5.99373867982851e-04 -3.51689007338519e-03 - 2.90086645599082e-04 -1.68425998144551e-03 - 7.80707788302466e-05 -4.44642161085781e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 4.70481559649517e-04 - 2.89878724192004e-04 1.85786145528648e-03 - 5.98775316682048e-04 4.14304619805457e-03 - 9.63326351634835e-04 6.97239817163410e-03 - 1.45966821282819e-03 1.00165826664615e-02 - 2.19097636449990e-03 1.28164596667998e-02 - 3.08997841959778e-03 1.54450452129794e-02 - 4.08271112470316e-03 1.77371439040307e-02 - 5.24853124383664e-03 2.01267946798734e-02 - 6.63128223001261e-03 2.27231841895761e-02 - 8.18368429859057e-03 2.52770362745904e-02 - 9.88361416849065e-03 2.77921030403423e-02 - 1.18176401547236e-02 3.04917252295171e-02 - 1.39661993216829e-02 3.32439391558398e-02 - 1.62951420791042e-02 3.60033476799753e-02 - 1.88631937781153e-02 3.88618386977883e-02 - 2.16807137532775e-02 4.17824735260288e-02 - 2.47159162958630e-02 4.47224462658207e-02 - 2.80064400105862e-02 4.76990146603553e-02 - 3.15762558914965e-02 5.07177063868115e-02 - 3.53948396168776e-02 5.37649854569942e-02 - 3.94949825480075e-02 5.68512841114507e-02 - 4.38979282781582e-02 5.99842429781050e-02 - 4.85758075737765e-02 6.31284365615533e-02 - 5.35679916138119e-02 6.62952383721983e-02 - 5.88818211488708e-02 6.94826798284928e-02 - 6.45001629027312e-02 7.26764876204622e-02 - 7.04692046391145e-02 7.58817499788644e-02 - 7.67740309924711e-02 7.90769134840093e-02 - 8.34162127168367e-02 8.22503653353708e-02 - 9.04290195190654e-02 8.54083423549473e-02 - 9.77906533229447e-02 8.85236648940710e-02 - 1.05536187198748e-01 9.15986556723743e-02 - 1.13658760041779e-01 9.46170785166153e-02 - 1.22161483318940e-01 9.75670687510333e-02 - 1.31067498602735e-01 1.00443723229551e-01 - 1.40354649921884e-01 1.03219272658907e-01 - 1.50055110786138e-01 1.05886276702156e-01 - 1.60148962661562e-01 1.08434273939193e-01 - 1.70658187899640e-01 1.10842785600643e-01 - 1.81574957422924e-01 1.13108243896473e-01 - 1.92907571409635e-01 1.15203325467163e-01 - 2.04657634577812e-01 1.17111809059137e-01 - 2.16817353069425e-01 1.18823832608443e-01 - 2.29396483963478e-01 1.20339521581196e-01 - 2.42377800694080e-01 1.21622855024966e-01 - 2.55773624268338e-01 1.22663079099559e-01 - 2.69566785632899e-01 1.23458490995195e-01 - 2.83765797226135e-01 1.23977807668107e-01 - 2.98347982887804e-01 1.24234503445114e-01 - 3.13318978785268e-01 1.24197635783805e-01 - 3.28658461892810e-01 1.23865322885844e-01 - 3.44364941645546e-01 1.23248038755391e-01 - 3.60419773725681e-01 1.22347481178388e-01 - 3.76811233766957e-01 1.21171439062179e-01 - 3.93525251020729e-01 1.19719504524330e-01 - 4.10538642553571e-01 1.18014256296836e-01 - 4.27843232490823e-01 1.16061982303762e-01 - 4.45406663468198e-01 1.13854843644173e-01 - 4.63222254103030e-01 1.11423391406499e-01 - 4.81251545655716e-01 1.08768658711877e-01 - 4.99481026671737e-01 1.05897548197613e-01 - 5.17879583085697e-01 1.02856689182191e-01 - 5.36417631367010e-01 9.96344202438156e-02 - 5.55075704909560e-01 9.62566007191012e-02 - 5.73808427242608e-01 9.27336081749321e-02 - 5.92596731105059e-01 8.90804155623268e-02 - 6.11401377553511e-01 8.53213583924465e-02 - 6.30186430605241e-01 8.14589286063343e-02 - 6.48926781663159e-01 7.75420194217522e-02 - 6.67570206424973e-01 7.35776020876609e-02 - 6.86088429590952e-01 6.96019917594570e-02 - 7.04445389043917e-01 6.56284162858813e-02 - 7.22592093722966e-01 6.16778469528591e-02 - 7.40501800453524e-01 5.77543537617252e-02 - 7.58125457122835e-01 5.39055305478617e-02 - 7.75421014376153e-01 5.01362014830259e-02 - 7.92362373587600e-01 4.64567188875079e-02 - 8.08894546151696e-01 4.28836623879816e-02 - 8.24974633014891e-01 3.94404092674687e-02 - 8.40576952273409e-01 3.61153248939489e-02 - 8.55652758808818e-01 3.29282825002114e-02 - 8.70162898882712e-01 2.98813936539527e-02 - 8.84085033071272e-01 2.69833550872399e-02 - 8.97361214262371e-01 2.42528760053068e-02 - 9.09954680076662e-01 2.16726032810659e-02 - 9.21851471402547e-01 1.92645200451516e-02 - 9.33012836658427e-01 1.70181285229120e-02 - 9.43389278969050e-01 1.49492212905369e-02 - 9.52973153850560e-01 1.30442406919280e-02 - 9.61743130827061e-01 1.13033926791581e-02 - 9.69640690675464e-01 9.73887915967785e-03 - 9.76664215898664e-01 8.34953370618003e-03 - 9.82815077112014e-01 7.13450005840548e-03 - 9.88028440045103e-01 6.10686015938910e-03 - 9.92304836603751e-01 5.26519515749948e-03 - 9.95693518775914e-01 4.59889670416978e-03 - 9.98120489340015e-01 4.12210942035042e-03 - 9.99443037908705e-01 3.86244188534050e-03 - 1.00000000000000e+00 3.75311683473109e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_33.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_33.dat index 44d98c6a..0906af09 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_33.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_33.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_33_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF33_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF33_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.886952 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.625187 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.714737 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.012741 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.829977 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.073708 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006540 Cd0 ! 2D drag coefficient value at 0-lift. - -0.084213 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.007721 Cd0 ! 2D drag coefficient value at 0-lift. +-0.084493 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 5.27632934953673e-03 1.37740905997295e-02 4.91630414281777e-03 --1.77714285740401e+02 6.06410875632402e-02 1.68982737683980e-02 9.15368383189179e-02 --1.75428571400002e+02 1.21999314443245e-01 1.69482885601424e-02 1.82518733879726e-01 --1.73142857116900e+02 1.76800841012212e-01 1.75010750858358e-02 2.74911796517862e-01 --1.70857160423602e+02 2.27709597114732e-01 2.30441584102975e-02 3.64991356173894e-01 --1.68571631778825e+02 2.77383644354552e-01 3.70840455760692e-02 3.94758858037247e-01 --1.66285714267592e+02 3.28492231038019e-01 5.92146765447896e-02 3.85742390243941e-01 --1.63999999984490e+02 3.83677074261421e-01 8.80408756709684e-02 3.75683380871914e-01 --1.61714472886699e+02 4.45593770012883e-01 1.22617804637408e-01 3.67880720495354e-01 --1.59428371284127e+02 5.15183495084243e-01 1.61471412976969e-01 3.65053674097241e-01 --1.57142842639350e+02 5.86358146398537e-01 2.03890892771535e-01 3.82191012816603e-01 --1.54857313994574e+02 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7.19648795062417e-19 1.35379551213142e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_33_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_33_Coords.txt deleted file mode 100644 index e60bdee0..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_33_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.295565 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -2.20146938989154e-03 - 9.99429683992583e-01 -2.12169982567663e-03 - 9.98063017832965e-01 -1.93245336040370e-03 - 9.95573914266674e-01 -1.59460483623308e-03 - 9.92086309749559e-01 -1.13567849202209e-03 - 9.87686148675057e-01 -5.80397310153661e-04 - 9.82330525170640e-01 6.36386905317887e-05 - 9.76011908335692e-01 7.82749117607113e-04 - 9.68787467298381e-01 1.55509243859155e-03 - 9.60674860259240e-01 2.36382722818551e-03 - 9.51675358763677e-01 3.19592440643064e-03 - 9.41827652746244e-01 4.03481116256730e-03 - 9.31175295355131e-01 4.78609328156652e-03 - 9.19730397431178e-01 5.37310571945470e-03 - 9.07524559194720e-01 5.76027603032651e-03 - 8.94610408070308e-01 5.88370027559244e-03 - 8.81009696499435e-01 5.73764023716248e-03 - 8.66747905197194e-01 5.27218338077900e-03 - 8.51890258171205e-01 4.48782615303993e-03 - 8.36469462621421e-01 3.33794434699119e-03 - 8.20513485943698e-01 1.80793464678944e-03 - 8.04073832217581e-01 -1.28987547635696e-04 - 7.87191529885653e-01 -2.53060463886510e-03 - 7.69897919101553e-01 -5.45952105699196e-03 - 7.52252341235159e-01 -8.87591916059599e-03 - 7.34291349178558e-01 -1.27755491652129e-02 - 7.16044924955764e-01 -1.71224046226949e-02 - 6.97571640033109e-01 -2.18818812509228e-02 - 6.78906186433687e-01 -2.70250389862613e-02 - 6.60080312620540e-01 -3.24930013059691e-02 - 6.41147517137212e-01 -3.82105727129863e-02 - 6.22137650968852e-01 -4.40990042965092e-02 - 6.03087998194415e-01 -5.00653994391748e-02 - 5.84045042118975e-01 -5.60374729950907e-02 - 5.65030897687003e-01 -6.19165458612377e-02 - 5.46088602779599e-01 -6.76314508880399e-02 - 5.27248673916899e-01 -7.31128762399586e-02 - 5.08535950506088e-01 -7.83003382901220e-02 - 4.89992355470388e-01 -8.31475329269395e-02 - 4.71632114506831e-01 -8.75766957752448e-02 - 4.53492503744347e-01 -9.15553853646277e-02 - 4.35593302897673e-01 -9.50620254429110e-02 - 4.17956065616942e-01 -9.81144485687851e-02 - 4.00609748442576e-01 -1.00693907486205e-01 - 3.83560931606009e-01 -1.02846278786083e-01 - 3.66843215733716e-01 -1.04558995100406e-01 - 3.50457316320503e-01 -1.05850934428343e-01 - 3.34434484008630e-01 -1.06750137766691e-01 - 3.18774100329315e-01 -1.07278617277178e-01 - 3.03499623121295e-01 -1.07442314718038e-01 - 2.88611293565648e-01 -1.07294359989106e-01 - 2.74124386665666e-01 -1.06813847623791e-01 - 2.60041455523719e-01 -1.06065910891659e-01 - 2.46374872015917e-01 -1.05050556567417e-01 - 2.33123443938834e-01 -1.03793763710843e-01 - 2.20293777810423e-01 -1.02318051375809e-01 - 2.07883282965331e-01 -1.00625971725334e-01 - 1.95902956391646e-01 -9.87536758056640e-02 - 1.84341253066628e-01 -9.66962936637641e-02 - 1.73213930954160e-01 -9.44957686530759e-02 - 1.62499176129638e-01 -9.21532763148740e-02 - 1.52214602777260e-01 -8.96891175023354e-02 - 1.42331759398971e-01 -8.71196345861815e-02 - 1.32872111539190e-01 -8.44757990454144e-02 - 1.23806439629760e-01 -8.17518548970172e-02 - 1.15147623386077e-01 -7.89701141210578e-02 - 1.06887208802748e-01 -7.61464747888819e-02 - 9.90071115215634e-02 -7.32820891940979e-02 - 9.15234043853439e-02 -7.04059827527966e-02 - 8.43970428172224e-02 -6.75221796404808e-02 - 7.76464790199521e-02 -6.46365172761336e-02 - 7.12479082120209e-02 -6.17667762610969e-02 - 6.51878662973747e-02 -5.89128701856431e-02 - 5.94874721274202e-02 -5.60919735200650e-02 - 5.41002464180900e-02 -5.33010527349436e-02 - 4.90378786701877e-02 -5.05542897467962e-02 - 4.43003497573338e-02 -4.78525124076741e-02 - 3.98423597346806e-02 -4.51880675576967e-02 - 3.56899752436130e-02 -4.25794508043144e-02 - 3.18292350050658e-02 -4.00337258491150e-02 - 2.82200072057899e-02 -3.75244268873699e-02 - 2.48925247792699e-02 -3.50906978374894e-02 - 2.18286683030034e-02 -3.27239725840001e-02 - 1.89846947131331e-02 -3.04127566847061e-02 - 1.63921917020335e-02 -2.81836193539164e-02 - 1.40446346341990e-02 -2.60061188861570e-02 - 1.18798249846349e-02 -2.38493849820612e-02 - 9.93094518736223e-03 -2.17546831256698e-02 - 8.21940795734749e-03 -1.97442555342267e-02 - 6.65838622137879e-03 -1.77637380458007e-02 - 5.26774192850643e-03 -1.60065318554002e-02 - 4.09515753852961e-03 -1.43187999865514e-02 - 3.09878859713640e-03 -1.25119355586005e-02 - 2.19660773551101e-03 -1.03488196099073e-02 - 1.46264176301869e-03 -7.78899194251944e-03 - 9.64484608297914e-04 -5.23807787628160e-03 - 5.99373867982851e-04 -3.21324024267837e-03 - 2.90086645599082e-04 -1.52618798575182e-03 - 7.80707788302466e-05 -3.99133000619684e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 4.33013884987675e-04 - 2.89878724192004e-04 1.66999978217974e-03 - 5.98775316682048e-04 3.74475960478147e-03 - 9.63326351634835e-04 6.43841589561363e-03 - 1.45966821282819e-03 9.43492183865405e-03 - 2.19097636449990e-03 1.22615126736163e-02 - 3.08997841959778e-03 1.48238248361314e-02 - 4.08271112470316e-03 1.70555086416697e-02 - 5.24853124383664e-03 1.93650486828735e-02 - 6.63128223001261e-03 2.18647059788978e-02 - 8.18368429859057e-03 2.43567898191181e-02 - 9.88361416849065e-03 2.68118646195546e-02 - 1.18176401547236e-02 2.94384418936377e-02 - 1.39661993216829e-02 3.21217062258930e-02 - 1.62951420791042e-02 3.48173770038145e-02 - 1.88631937781153e-02 3.76082471342302e-02 - 2.16807137532775e-02 4.04643664277869e-02 - 2.47159162958630e-02 4.33426265010939e-02 - 2.80064400105862e-02 4.62609118296159e-02 - 3.15762558914965e-02 4.92210354566621e-02 - 3.53948396168776e-02 5.22050295151951e-02 - 3.94949825480075e-02 5.52309366873118e-02 - 4.38979282781582e-02 5.83060961893335e-02 - 4.85758075737765e-02 6.13972262705384e-02 - 5.35679916138119e-02 6.45134091853517e-02 - 5.88818211488708e-02 6.76552298677320e-02 - 6.45001629027312e-02 7.08071967728573e-02 - 7.04692046391145e-02 7.39744117153368e-02 - 7.67740309924711e-02 7.71358005856310e-02 - 8.34162127168367e-02 8.02790092795951e-02 - 9.04290195190654e-02 8.34115038572756e-02 - 9.77906533229447e-02 8.65046592309233e-02 - 1.05536187198748e-01 8.95648602960541e-02 - 1.13658760041779e-01 9.25761140854296e-02 - 1.22161483318940e-01 9.55223973858629e-02 - 1.31067498602735e-01 9.84008425735129e-02 - 1.40354649921884e-01 1.01181300628542e-01 - 1.50055110786138e-01 1.03863158861816e-01 - 1.60148962661562e-01 1.06438262758006e-01 - 1.70658187899640e-01 1.08865906371866e-01 - 1.81574957422924e-01 1.11169596986812e-01 - 1.92907571409635e-01 1.13305115579809e-01 - 2.04657634577812e-01 1.15257087912737e-01 - 2.16817353069425e-01 1.17018160424267e-01 - 2.29396483963478e-01 1.18595120683331e-01 - 2.42377800694080e-01 1.19933494690816e-01 - 2.55773624268338e-01 1.21022587555683e-01 - 2.69566785632899e-01 1.21865099644109e-01 - 2.83765797226135e-01 1.22433850868887e-01 - 2.98347982887804e-01 1.22745161092091e-01 - 3.13318978785268e-01 1.22742543625482e-01 - 3.28658461892810e-01 1.22448316560108e-01 - 3.44364941645546e-01 1.21850164431836e-01 - 3.60419773725681e-01 1.20973095676634e-01 - 3.76811233766957e-01 1.19812259132660e-01 - 3.93525251020729e-01 1.18369040124414e-01 - 4.10538642553571e-01 1.16665407882111e-01 - 4.27843232490823e-01 1.14723502979731e-01 - 4.45406663468198e-01 1.12511433954166e-01 - 4.63222254103030e-01 1.10080860675541e-01 - 4.81251545655716e-01 1.07415542525644e-01 - 4.99481026671737e-01 1.04537721633457e-01 - 5.17879583085697e-01 1.01499102795557e-01 - 5.36417631367010e-01 9.82697400828387e-02 - 5.55075704909560e-01 9.48856546243368e-02 - 5.73808427242608e-01 9.13583013647443e-02 - 5.92596731105059e-01 8.76987913761146e-02 - 6.11401377553511e-01 8.39333147242793e-02 - 6.30186430605241e-01 8.00609491321030e-02 - 6.48926781663159e-01 7.61400542245406e-02 - 6.67570206424973e-01 7.21725867699220e-02 - 6.86088429590952e-01 6.81995685834561e-02 - 7.04445389043917e-01 6.42271908433278e-02 - 7.22592093722966e-01 6.02875254850117e-02 - 7.40501800453524e-01 5.63752553837309e-02 - 7.58125457122835e-01 5.25433930961208e-02 - 7.75421014376153e-01 4.87966139172842e-02 - 7.92362373587600e-01 4.51437738568790e-02 - 8.08894546151696e-01 4.16024708514441e-02 - 8.24974633014891e-01 3.81951468927799e-02 - 8.40576952273409e-01 3.49092285658599e-02 - 8.55652758808818e-01 3.17626568742459e-02 - 8.70162898882712e-01 2.87554444344011e-02 - 8.84085033071272e-01 2.59014253959004e-02 - 8.97361214262371e-01 2.32125950364591e-02 - 9.09954680076662e-01 2.06765284299007e-02 - 9.21851471402547e-01 1.83107323344040e-02 - 9.33012836658427e-01 1.61066664143365e-02 - 9.43389278969050e-01 1.40771974712573e-02 - 9.52973153850560e-01 1.22140401915576e-02 - 9.61743130827061e-01 1.05133487330020e-02 - 9.69640690675464e-01 8.98731348695519e-03 - 9.76664215898664e-01 7.63388489323570e-03 - 9.82815077112014e-01 6.45174441106355e-03 - 9.88028440045103e-01 5.45358035778552e-03 - 9.92304836603751e-01 4.63709417327259e-03 - 9.95693518775914e-01 3.99131461581716e-03 - 9.98120489340015e-01 3.52956418969027e-03 - 9.99443037908705e-01 3.27821541308979e-03 - 1.00000000000000e+00 3.17241987256682e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_34.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_34.dat index 6173b9b6..a0a0c685 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_34.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_34.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_34_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF34_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF34_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.928166 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-12.912500 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.699261 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.019155 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.815093 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.091026 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006524 Cd0 ! 2D drag coefficient value at 0-lift. - -0.083024 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.007431 Cd0 ! 2D drag coefficient value at 0-lift. +-0.083329 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 3.21760667475586e-03 1.61550636996382e-02 4.91257289603857e-03 --1.77714285740401e+02 5.97333520981253e-02 1.88440849579556e-02 9.15263047171746e-02 --1.75428571400002e+02 1.20193204544779e-01 1.90953839653892e-02 1.82552980750820e-01 --1.73142857116900e+02 1.74274130910013e-01 2.03901805790903e-02 2.74845797268629e-01 --1.70857160423602e+02 2.24564936923219e-01 2.68052519529209e-02 3.65069141469664e-01 --1.68571631778825e+02 2.73649327898844e-01 4.15142999728000e-02 3.94023705463168e-01 --1.66285714267592e+02 3.24123068028802e-01 6.40904774732515e-02 3.83824259560830e-01 --1.63999999984490e+02 3.78555291076616e-01 9.31955172768017e-02 3.72869775768654e-01 --1.61714472886699e+02 4.39528413258921e-01 1.27831061169303e-01 3.63682446556930e-01 --1.59428371284127e+02 5.07958469281030e-01 1.66640469394291e-01 3.60132955343878e-01 --1.57142842639350e+02 5.77932330517757e-01 2.08979601446248e-01 3.77147677129081e-01 --1.54857313994574e+02 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1.71825147130708e-18 1.60687387137002e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_34_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_34_Coords.txt deleted file mode 100644 index d6dd14ef..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_34_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.297982 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -1.65532810836204e-03 - 9.99429683992583e-01 -1.58110469498104e-03 - 9.98063017832965e-01 -1.40497738734703e-03 - 9.95573914266674e-01 -1.09040359464525e-03 - 9.92086309749559e-01 -6.62787524340167e-04 - 9.87686148675057e-01 -1.44981903895491e-04 - 9.82330525170640e-01 4.56593004813578e-04 - 9.76011908335692e-01 1.13014409473121e-03 - 9.68787467298381e-01 1.85637380690860e-03 - 9.60674860259240e-01 2.62079527101689e-03 - 9.51675358763677e-01 3.41311737766908e-03 - 9.41827652746244e-01 4.21947274565506e-03 - 9.31175295355131e-01 4.94869119269752e-03 - 9.19730397431178e-01 5.50709454148093e-03 - 9.07524559194720e-01 5.87309971442215e-03 - 8.94610408070308e-01 5.98721017459064e-03 - 8.81009696499435e-01 5.84360771303102e-03 - 8.66747905197194e-01 5.39754400013184e-03 - 8.51890258171205e-01 4.64419247768644e-03 - 8.36469462621421e-01 3.53623863855826e-03 - 8.20513485943698e-01 2.06643478965616e-03 - 8.04073832217581e-01 2.09140167405660e-04 - 7.87191529885653e-01 -2.08932672020872e-03 - 7.69897919101553e-01 -4.90479920199649e-03 - 7.52252341235159e-01 -8.17595934947790e-03 - 7.34291349178558e-01 -1.19016596633065e-02 - 7.16044924955764e-01 -1.60548617066014e-02 - 6.97571640033109e-01 -2.06035514150126e-02 - 6.78906186433687e-01 -2.55225591986212e-02 - 6.60080312620540e-01 -3.07585426915617e-02 - 6.41147517137212e-01 -3.62407960661957e-02 - 6.22137650968852e-01 -4.18989241079043e-02 - 6.03087998194415e-01 -4.76447760546151e-02 - 5.84045042118975e-01 -5.34125840272090e-02 - 5.65030897687003e-01 -5.90992318407062e-02 - 5.46088602779599e-01 -6.46403605631713e-02 - 5.27248673916899e-01 -6.99660014622200e-02 - 5.08535950506088e-01 -7.50221124313659e-02 - 4.89992355470388e-01 -7.97525409488622e-02 - 4.71632114506831e-01 -8.40715831930243e-02 - 4.53492503744347e-01 -8.79478817541612e-02 - 4.35593302897673e-01 -9.13562036210487e-02 - 4.17956065616942e-01 -9.43117764715699e-02 - 4.00609748442576e-01 -9.67991405024225e-02 - 3.83560931606009e-01 -9.88641594104040e-02 - 3.66843215733716e-01 -1.00498946296538e-01 - 3.50457316320503e-01 -1.01717885858151e-01 - 3.34434484008630e-01 -1.02553902581934e-01 - 3.18774100329315e-01 -1.03023485548627e-01 - 3.03499623121295e-01 -1.03138156090871e-01 - 2.88611293565648e-01 -1.02950391948282e-01 - 2.74124386665666e-01 -1.02441357762369e-01 - 2.60041455523719e-01 -1.01673565383746e-01 - 2.46374872015917e-01 -1.00653010652197e-01 - 2.33123443938834e-01 -9.93985699975185e-02 - 2.20293777810423e-01 -9.79368543988111e-02 - 2.07883282965331e-01 -9.62739562089367e-02 - 1.95902956391646e-01 -9.44394949934210e-02 - 1.84341253066628e-01 -9.24309108291088e-02 - 1.73213930954160e-01 -9.02880838501478e-02 - 1.62499176129638e-01 -8.80161165487224e-02 - 1.52214602777260e-01 -8.56298080929594e-02 - 1.42331759398971e-01 -8.31495404618267e-02 - 1.32872111539190e-01 -8.06039859187970e-02 - 1.23806439629760e-01 -7.79853916733036e-02 - 1.15147623386077e-01 -7.53179418499888e-02 - 1.06887208802748e-01 -7.26122140025815e-02 - 9.90071115215634e-02 -6.98718035461578e-02 - 9.15234043853439e-02 -6.71229337456591e-02 - 8.43970428172224e-02 -6.43691278768861e-02 - 7.76464790199521e-02 -6.16164190886042e-02 - 7.12479082120209e-02 -5.88807380282725e-02 - 6.51878662973747e-02 -5.61626702984503e-02 - 5.94874721274202e-02 -5.34801000957454e-02 - 5.41002464180900e-02 -5.08266583868022e-02 - 4.90378786701877e-02 -4.82134186432125e-02 - 4.43003497573338e-02 -4.56418007192256e-02 - 3.98423597346806e-02 -4.31058927075264e-02 - 3.56899752436130e-02 -4.06232127412395e-02 - 3.18292350050658e-02 -3.82005049202423e-02 - 2.82200072057899e-02 -3.58139704975880e-02 - 2.48925247792699e-02 -3.34973687768432e-02 - 2.18286683030034e-02 -3.12482554812768e-02 - 1.89846947131331e-02 -2.90483092118643e-02 - 1.63921917020335e-02 -2.69229404059269e-02 - 1.40446346341990e-02 -2.48587775814658e-02 - 1.18798249846349e-02 -2.28140609626170e-02 - 9.93094518736223e-03 -2.08193382478191e-02 - 8.21940795734749e-03 -1.89172149883323e-02 - 6.65838622137879e-03 -1.70706462153181e-02 - 5.26774192850643e-03 -1.53897831405549e-02 - 4.09515753852961e-03 -1.37482370951108e-02 - 3.09878859713640e-03 -1.19923931559637e-02 - 2.19660773551101e-03 -9.85806292496550e-03 - 1.46264176301869e-03 -7.29183618134012e-03 - 9.64484608297914e-04 -4.84783473089480e-03 - 5.99373867982851e-04 -2.94415221623123e-03 - 2.90086645599082e-04 -1.38916950608740e-03 - 7.80707788302466e-05 -3.60884243488222e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.97593408911395e-04 - 2.89878724192004e-04 1.50620073161537e-03 - 5.98775316682048e-04 3.38755336458370e-03 - 9.63326351634835e-04 5.90285751476223e-03 - 1.45966821282819e-03 8.79898909274454e-03 - 2.19097636449990e-03 1.16494777707500e-02 - 3.08997841959778e-03 1.41362539894476e-02 - 4.08271112470316e-03 1.63126801204048e-02 - 5.24853124383664e-03 1.85351363020707e-02 - 6.63128223001261e-03 2.09212577831784e-02 - 8.18368429859057e-03 2.33490791359592e-02 - 9.88361416849065e-03 2.57464018287979e-02 - 1.18176401547236e-02 2.82938980954754e-02 - 1.39661993216829e-02 3.09050641611512e-02 - 1.62951420791042e-02 3.35363488015605e-02 - 1.88631937781153e-02 3.62555003405305e-02 - 2.16807137532775e-02 3.90440064141549e-02 - 2.47159162958630e-02 4.18578463076720e-02 - 2.80064400105862e-02 4.47154041989373e-02 - 3.15762558914965e-02 4.76211834549412e-02 - 3.53948396168776e-02 5.05500329854233e-02 - 3.94949825480075e-02 5.35241686520981e-02 - 4.38979282781582e-02 5.65492422359552e-02 - 4.85758075737765e-02 5.95938078067134e-02 - 5.35679916138119e-02 6.26661434240876e-02 - 5.88818211488708e-02 6.57692777701898e-02 - 6.45001629027312e-02 6.88857334910618e-02 - 7.04692046391145e-02 7.20215347596879e-02 - 7.67740309924711e-02 7.51556736357007e-02 - 8.34162127168367e-02 7.82755858191277e-02 - 9.04290195190654e-02 8.13889363061572e-02 - 9.77906533229447e-02 8.44666451572440e-02 - 1.05536187198748e-01 8.75190757684227e-02 - 1.13658760041779e-01 9.05308649950035e-02 - 1.22161483318940e-01 9.34807595685673e-02 - 1.31067498602735e-01 9.63679436428741e-02 - 1.40354649921884e-01 9.91594806356807e-02 - 1.50055110786138e-01 1.01863998726009e-01 - 1.60148962661562e-01 1.04474587672697e-01 - 1.70658187899640e-01 1.06926234528142e-01 - 1.81574957422924e-01 1.09276062062053e-01 - 1.92907571409635e-01 1.11459048583310e-01 - 2.04657634577812e-01 1.13460525970178e-01 - 2.16817353069425e-01 1.15276393429802e-01 - 2.29396483963478e-01 1.16921569864390e-01 - 2.42377800694080e-01 1.18320276784109e-01 - 2.55773624268338e-01 1.19461580669032e-01 - 2.69566785632899e-01 1.20353311559081e-01 - 2.83765797226135e-01 1.20974547326248e-01 - 2.98347982887804e-01 1.21343724514101e-01 - 3.13318978785268e-01 1.21375218655883e-01 - 3.28658461892810e-01 1.21120711218692e-01 - 3.44364941645546e-01 1.20539922212582e-01 - 3.60419773725681e-01 1.19685490934338e-01 - 3.76811233766957e-01 1.18538051572851e-01 - 3.93525251020729e-01 1.17100973476216e-01 - 4.10538642553571e-01 1.15395028633351e-01 - 4.27843232490823e-01 1.13460958142571e-01 - 4.45406663468198e-01 1.11238839003000e-01 - 4.63222254103030e-01 1.08805159456943e-01 - 4.81251545655716e-01 1.06122474010302e-01 - 4.99481026671737e-01 1.03232419550929e-01 - 5.17879583085697e-01 1.00191474360658e-01 - 5.36417631367010e-01 9.69489056598973e-02 - 5.55075704909560e-01 9.35520923675190e-02 - 5.73808427242608e-01 9.00144640224496e-02 - 5.92596731105059e-01 8.63425577470127e-02 - 6.11401377553511e-01 8.25638135305448e-02 - 6.30186430605241e-01 7.86740018566210e-02 - 6.48926781663159e-01 7.47420623357498e-02 - 6.67570206424973e-01 7.07644449433777e-02 - 6.86088429590952e-01 6.67874624016192e-02 - 7.04445389043917e-01 6.28078191306311e-02 - 7.22592093722966e-01 5.88724147769271e-02 - 7.40501800453524e-01 5.49645342305940e-02 - 7.58125457122835e-01 5.11427116378125e-02 - 7.75421014376153e-01 4.74119669836773e-02 - 7.92362373587600e-01 4.37800696085148e-02 - 8.08894546151696e-01 4.02653500089241e-02 - 8.24974633014891e-01 3.68889789485175e-02 - 8.40576952273409e-01 3.36390014270195e-02 - 8.55652758808818e-01 3.05291942360335e-02 - 8.70162898882712e-01 2.75581805989511e-02 - 8.84085033071272e-01 2.47469990800409e-02 - 8.97361214262371e-01 2.20973915514803e-02 - 9.09954680076662e-01 1.96059421910381e-02 - 9.21851471402547e-01 1.72818190024409e-02 - 9.33012836658427e-01 1.51219022032212e-02 - 9.43389278969050e-01 1.31334498018886e-02 - 9.52973153850560e-01 1.13161159747796e-02 - 9.61743130827061e-01 9.65975375102014e-03 - 9.69640690675464e-01 8.17607236671208e-03 - 9.76664215898664e-01 6.86257786273574e-03 - 9.82815077112014e-01 5.71739116372332e-03 - 9.88028440045103e-01 4.75214905226014e-03 - 9.92304836603751e-01 3.96384524388564e-03 - 9.95693518775914e-01 3.34119485466673e-03 - 9.98120489340015e-01 2.89645895827774e-03 - 9.99443037908705e-01 2.65454534302132e-03 - 1.00000000000000e+00 2.55275775544748e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_35.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_35.dat index 0cd91a25..9c13bcd5 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_35.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_35.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_35_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF35_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF35_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -2.974289 alpha0 ! 0-lift angle of attack, depends on airfoil. - 12.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -12.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-13.294942 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.680061 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.027332 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.797456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.107962 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006524 Cd0 ! 2D drag coefficient value at 0-lift. - -0.081698 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.007178 Cd0 ! 2D drag coefficient value at 0-lift. +-0.081997 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 7.27929612187732e-05 1.89316714848307e-02 4.90807680580429e-03 --1.77714285740401e+02 5.89164628122001e-02 2.11361488592876e-02 9.15134344314018e-02 --1.75428571400002e+02 1.18568879509543e-01 2.16187172128167e-02 1.82595041982651e-01 --1.73142857116900e+02 1.71979912350637e-01 2.37674196567954e-02 2.74763621772468e-01 --1.70857160423602e+02 2.21678751067750e-01 3.11776900724915e-02 3.65168201933801e-01 --1.68571631778825e+02 2.70190645368349e-01 4.66333992977384e-02 3.93316141013364e-01 --1.66285714267592e+02 3.20054350159146e-01 6.96841825538760e-02 3.81983802981344e-01 --1.63999999984490e+02 3.73783203294858e-01 9.90594966034864e-02 3.70260496963796e-01 --1.61714472886699e+02 4.33902970448130e-01 1.33658878863484e-01 3.59676108783954e-01 --1.59428371284127e+02 5.01310375605851e-01 1.72289264363216e-01 3.55485119355648e-01 --1.57142842639350e+02 5.70232943533333e-01 2.14403954472022e-01 3.72351177590766e-01 --1.54857313994574e+02 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2.88598621586899e-18 1.91400298203920e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_35_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_35_Coords.txt deleted file mode 100644 index 36b70890..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_35_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.300597 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -1.15647386219963e-03 - 9.99429683992583e-01 -1.08812035753760e-03 - 9.98063017832965e-01 -9.25815572813168e-04 - 9.95573914266674e-01 -6.35540300230506e-04 - 9.92086309749559e-01 -2.40135910637772e-04 - 9.87686148675057e-01 2.40033902582720e-04 - 9.82330525170640e-01 7.99631634387703e-04 - 9.76011908335692e-01 1.42844568104934e-03 - 9.68787467298381e-01 2.10939474904413e-03 - 9.60674860259240e-01 2.82999207609742e-03 - 9.51675358763677e-01 3.58178307479687e-03 - 9.41827652746244e-01 4.35322371372933e-03 - 9.31175295355131e-01 5.06012255611244e-03 - 9.19730397431178e-01 5.59744506239930e-03 - 9.07524559194720e-01 5.94804107195984e-03 - 8.94610408070308e-01 6.05536818055086e-03 - 8.81009696499435e-01 5.91313077704495e-03 - 8.66747905197194e-01 5.48011426765490e-03 - 8.51890258171205e-01 4.74785261695384e-03 - 8.36469462621421e-01 3.66867713831287e-03 - 8.20513485943698e-01 2.24076227228030e-03 - 8.04073832217581e-01 4.39522493060134e-04 - 7.87191529885653e-01 -1.78183691759181e-03 - 7.69897919101553e-01 -4.49764162239654e-03 - 7.52252341235159e-01 -7.63675190295551e-03 - 7.34291349178558e-01 -1.11997711953664e-02 - 7.16044924955764e-01 -1.51693525274012e-02 - 6.97571640033109e-01 -1.95157701133580e-02 - 6.78906186433687e-01 -2.42175539528326e-02 - 6.60080312620540e-01 -2.92270710992370e-02 - 6.41147517137212e-01 -3.44782966931651e-02 - 6.22137650968852e-01 -3.99097102950896e-02 - 6.03087998194415e-01 -4.54381119698041e-02 - 5.84045042118975e-01 -5.10048432872634e-02 - 5.65030897687003e-01 -5.65013848127218e-02 - 5.46088602779599e-01 -6.18710866274905e-02 - 5.27248673916899e-01 -6.70432429110530e-02 - 5.08535950506088e-01 -7.19715635339354e-02 - 4.89992355470388e-01 -7.65879201622483e-02 - 4.71632114506831e-01 -8.07992353921352e-02 - 4.53492503744347e-01 -8.45759191449691e-02 - 4.35593302897673e-01 -8.78886852139242e-02 - 4.17956065616942e-01 -9.07492081621322e-02 - 4.00609748442576e-01 -9.31471109092231e-02 - 3.83560931606009e-01 -9.51260874253568e-02 - 3.66843215733716e-01 -9.66848292130680e-02 - 3.50457316320503e-01 -9.78321211216180e-02 - 3.34434484008630e-01 -9.86063967707739e-02 - 3.18774100329315e-01 -9.90177825640367e-02 - 3.03499623121295e-01 -9.90840625771335e-02 - 2.88611293565648e-01 -9.88565404292377e-02 - 2.74124386665666e-01 -9.83197143147713e-02 - 2.60041455523719e-01 -9.75315529472340e-02 - 2.46374872015917e-01 -9.65055925334341e-02 - 2.33123443938834e-01 -9.52526802950054e-02 - 2.20293777810423e-01 -9.38033005606699e-02 - 2.07883282965331e-01 -9.21687611540636e-02 - 1.95902956391646e-01 -9.03702281144066e-02 - 1.84341253066628e-01 -8.84083236019629e-02 - 1.73213930954160e-01 -8.63201286812817e-02 - 1.62499176129638e-01 -8.41156520126071e-02 - 1.52214602777260e-01 -8.18037371917952e-02 - 1.42331759398971e-01 -7.94091962081510e-02 - 1.32872111539190e-01 -7.69575622996747e-02 - 1.23806439629760e-01 -7.44398645315319e-02 - 1.15147623386077e-01 -7.18819272636878e-02 - 1.06887208802748e-01 -6.92886702885704e-02 - 9.90071115215634e-02 -6.66667131030478e-02 - 9.15234043853439e-02 -6.40394815772871e-02 - 8.43970428172224e-02 -6.14089466212372e-02 - 7.76464790199521e-02 -5.87827675608139e-02 - 7.12479082120209e-02 -5.61737162421853e-02 - 6.51878662973747e-02 -5.35838743201633e-02 - 5.94874721274202e-02 -5.10319163241668e-02 - 5.41002464180900e-02 -4.85076071867253e-02 - 4.90378786701877e-02 -4.60194251387520e-02 - 4.43003497573338e-02 -4.35711561558663e-02 - 3.98423597346806e-02 -4.11569714821332e-02 - 3.56899752436130e-02 -3.87935150274630e-02 - 3.18292350050658e-02 -3.64869896117962e-02 - 2.82200072057899e-02 -3.42165209086429e-02 - 2.48925247792699e-02 -3.20098891529479e-02 - 2.18286683030034e-02 -2.98714220294968e-02 - 1.89846947131331e-02 -2.77746429668576e-02 - 1.63921917020335e-02 -2.57445698076921e-02 - 1.40446346341990e-02 -2.37891391177558e-02 - 1.18798249846349e-02 -2.18507261143834e-02 - 9.93094518736223e-03 -1.99484253477475e-02 - 8.21940795734749e-03 -1.81491133463558e-02 - 6.65838622137879e-03 -1.64341659606168e-02 - 5.26774192850643e-03 -1.48155949840070e-02 - 4.09515753852961e-03 -1.32032268836932e-02 - 3.09878859713640e-03 -1.14900254604776e-02 - 2.19660773551101e-03 -9.38896778865496e-03 - 1.46264176301869e-03 -6.82351671991761e-03 - 9.64484608297914e-04 -4.51443287953383e-03 - 5.99373867982851e-04 -2.73563330377491e-03 - 2.90086645599082e-04 -1.28872221655481e-03 - 7.80707788302466e-05 -3.34826091767089e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.67007748448927e-04 - 2.89878724192004e-04 1.38415087173582e-03 - 5.98775316682048e-04 3.10380359832384e-03 - 9.63326351634835e-04 5.40914744892566e-03 - 1.45966821282819e-03 8.17152174306766e-03 - 2.19097636449990e-03 1.10421536838056e-02 - 3.08997841959778e-03 1.34524245106757e-02 - 4.08271112470316e-03 1.55813160241666e-02 - 5.24853124383664e-03 1.77181765572298e-02 - 6.63128223001261e-03 1.99872056287348e-02 - 8.18368429859057e-03 2.23537396881755e-02 - 9.88361416849065e-03 2.46992168739366e-02 - 1.18176401547236e-02 2.71691977681130e-02 - 1.39661993216829e-02 2.97113979833503e-02 - 1.62951420791042e-02 3.22826791634240e-02 - 1.88631937781153e-02 3.49325395746672e-02 - 2.16807137532775e-02 3.76562844105083e-02 - 2.47159162958630e-02 4.04086044195530e-02 - 2.80064400105862e-02 4.32082521017065e-02 - 3.15762558914965e-02 4.60669789727449e-02 - 3.53948396168776e-02 4.89510667122300e-02 - 3.94949825480075e-02 5.18840559985377e-02 - 4.38979282781582e-02 5.48689620113342e-02 - 4.85758075737765e-02 5.78757478102759e-02 - 5.35679916138119e-02 6.09130989463105e-02 - 5.88818211488708e-02 6.39862055572016e-02 - 6.45001629027312e-02 6.70751325150091e-02 - 7.04692046391145e-02 7.01874836666141e-02 - 7.67740309924711e-02 7.33019708871667e-02 - 8.34162127168367e-02 7.64062777993611e-02 - 9.04290195190654e-02 7.95073846528665e-02 - 9.77906533229447e-02 8.25766265837654e-02 - 1.05536187198748e-01 8.56279602349445e-02 - 1.13658760041779e-01 8.86469463367283e-02 - 1.22161483318940e-01 9.16065960078561e-02 - 1.31067498602735e-01 9.45079856730387e-02 - 1.40354649921884e-01 9.73152413516494e-02 - 1.50055110786138e-01 1.00047667119421e-01 - 1.60148962661562e-01 1.02698577303576e-01 - 1.70658187899640e-01 1.05176821717740e-01 - 1.81574957422924e-01 1.07576513503073e-01 - 1.92907571409635e-01 1.09809879928672e-01 - 2.04657634577812e-01 1.11862744409664e-01 - 2.16817353069425e-01 1.13734710623184e-01 - 2.29396483963478e-01 1.15449680634554e-01 - 2.42377800694080e-01 1.16909413592453e-01 - 2.55773624268338e-01 1.18102363600292e-01 - 2.69566785632899e-01 1.19041776640665e-01 - 2.83765797226135e-01 1.19714765439433e-01 - 2.98347982887804e-01 1.20141004366885e-01 - 3.13318978785268e-01 1.20203950956058e-01 - 3.28658461892810e-01 1.19988062381970e-01 - 3.44364941645546e-01 1.19421424608530e-01 - 3.60419773725681e-01 1.18587049832099e-01 - 3.76811233766957e-01 1.17450039903988e-01 - 3.93525251020729e-01 1.16015826839961e-01 - 4.10538642553571e-01 1.14303465554320e-01 - 4.27843232490823e-01 1.12373916704757e-01 - 4.45406663468198e-01 1.10137047888005e-01 - 4.63222254103030e-01 1.07696314803450e-01 - 4.81251545655716e-01 1.04990596204181e-01 - 4.99481026671737e-01 1.02083665832523e-01 - 5.17879583085697e-01 9.90360188671852e-02 - 5.36417631367010e-01 9.57752734433290e-02 - 5.55075704909560e-01 9.23604940030636e-02 - 5.73808427242608e-01 8.88077818743235e-02 - 5.92596731105059e-01 8.51187724465540e-02 - 6.11401377553511e-01 8.13215038955476e-02 - 6.30186430605241e-01 7.74088299058529e-02 - 6.48926781663159e-01 7.34604260824622e-02 - 6.67570206424973e-01 6.94672237318301e-02 - 6.86088429590952e-01 6.54809001035560e-02 - 7.04445389043917e-01 6.14873309292957e-02 - 7.22592093722966e-01 5.75502392859803e-02 - 7.40501800453524e-01 5.36407034062524e-02 - 7.58125457122835e-01 4.98224265942367e-02 - 7.75421014376153e-01 4.61011505665179e-02 - 7.92362373587600e-01 4.24839635839417e-02 - 8.08894546151696e-01 3.89896284863811e-02 - 8.24974633014891e-01 3.56378763237775e-02 - 8.40576952273409e-01 3.24185246732406e-02 - 8.55652758808818e-01 2.93397722206353e-02 - 8.70162898882712e-01 2.63995114605996e-02 - 8.84085033071272e-01 2.36269761561548e-02 - 8.97361214262371e-01 2.10117741800041e-02 - 9.09954680076662e-01 1.85618430396294e-02 - 9.21851471402547e-01 1.62757758428789e-02 - 9.33012836658427e-01 1.41580022685561e-02 - 9.43389278969050e-01 1.22086215660364e-02 - 9.52973153850560e-01 1.04365697115066e-02 - 9.61743130827061e-01 8.82423469374550e-03 - 9.69640690675464e-01 7.38253855145307e-03 - 9.76664215898664e-01 6.10889810892982e-03 - 9.82815077112014e-01 5.00084651408543e-03 - 9.88028440045103e-01 4.06856494607742e-03 - 9.92304836603751e-01 3.30851897139796e-03 - 9.95693518775914e-01 2.70917022529484e-03 - 9.98120489340015e-01 2.28162068318196e-03 - 9.99443037908705e-01 2.04925317932011e-03 - 1.00000000000000e+00 1.95152405080697e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_36.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_36.dat index 4d0007a3..dae26ecf 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_36.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_36.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_36_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF36_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF36_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.016542 alpha0 ! 0-lift angle of attack, depends on airfoil. - 12.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -12.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-13.697518 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.660918 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.035669 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.781001 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.122153 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006539 Cd0 ! 2D drag coefficient value at 0-lift. - -0.080467 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006983 Cd0 ! 2D drag coefficient value at 0-lift. +-0.080790 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -3.61078103437437e-03 2.15357655087037e-02 4.90371714029576e-03 --1.77714285740401e+02 5.82563837773996e-02 2.33084274188512e-02 9.15007851887650e-02 --1.75428571400002e+02 1.17257158483554e-01 2.40044806424730e-02 1.82636585505883e-01 --1.73142857116900e+02 1.70110470452195e-01 2.69427852977837e-02 2.74681411442098e-01 --1.70857160423602e+02 2.19304068566442e-01 3.52650260377885e-02 3.65269347055498e-01 --1.68571631778825e+02 2.67322586958365e-01 5.13877608572627e-02 3.92711853351261e-01 --1.66285714267592e+02 3.16665159258330e-01 7.48392825675415e-02 3.80415371587819e-01 --1.63999999984490e+02 3.69806404564519e-01 1.04413905376931e-01 3.68094459799131e-01 --1.61714472886699e+02 4.29232742054421e-01 1.38956048428370e-01 3.56275227115608e-01 --1.59428371284127e+02 4.95828300156015e-01 1.77402843174190e-01 3.51569736113746e-01 --1.57142842639350e+02 5.63922696960420e-01 2.19281483558668e-01 3.68289628014895e-01 --1.54857313994574e+02 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3.94500701911350e-18 2.20397515249612e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_36_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_36_Coords.txt deleted file mode 100644 index 7c8944cd..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_36_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.303407 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -7.47772149606326e-04 - 9.99429683992583e-01 -6.84820230418506e-04 - 9.98063017832965e-01 -5.35205246947433e-04 - 9.95573914266674e-01 -2.67125461477943e-04 - 9.92086309749559e-01 9.91082174024997e-05 - 9.87686148675057e-01 5.45745402853979e-04 - 9.82330525170640e-01 1.06832515546379e-03 - 9.76011908335692e-01 1.65778785254992e-03 - 9.68787467298381e-01 2.29872677680581e-03 - 9.60674860259240e-01 2.98007801005491e-03 - 9.51675358763677e-01 3.69412295205826e-03 - 9.41827652746244e-01 4.43082539957194e-03 - 9.31175295355131e-01 5.11659957504717e-03 - 9.19730397431178e-01 5.64270591380843e-03 - 9.07524559194720e-01 5.98516596429100e-03 - 8.94610408070308e-01 6.08891064913623e-03 - 8.81009696499435e-01 5.94725000840259e-03 - 8.66747905197194e-01 5.52075851646691e-03 - 8.51890258171205e-01 4.79912858987679e-03 - 8.36469462621421e-01 3.73455490700237e-03 - 8.20513485943698e-01 2.32809748012341e-03 - 8.04073832217581e-01 5.55803460868978e-04 - 7.87191529885653e-01 -1.61966230388234e-03 - 7.69897919101553e-01 -4.25437704244268e-03 - 7.52252341235159e-01 -7.28263727663909e-03 - 7.34291349178558e-01 -1.07061354128477e-02 - 7.16044924955764e-01 -1.45173533332810e-02 - 6.97571640033109e-01 -1.86883999555379e-02 - 6.78906186433687e-01 -2.32010584969707e-02 - 6.60080312620540e-01 -2.80128741485589e-02 - 6.41147517137212e-01 -3.30620395201012e-02 - 6.22137650968852e-01 -3.82951674530533e-02 - 6.03087998194415e-01 -4.36334580745152e-02 - 5.84045042118975e-01 -4.90248233322585e-02 - 5.65030897687003e-01 -5.43552521459939e-02 - 5.46088602779599e-01 -5.95754364624474e-02 - 5.27248673916899e-01 -6.46139190466105e-02 - 5.08535950506088e-01 -6.94320338659525e-02 - 4.89992355470388e-01 -7.39497255715813e-02 - 4.71632114506831e-01 -7.80677847769374e-02 - 4.53492503744347e-01 -8.17586026275836e-02 - 4.35593302897673e-01 -8.49890726311646e-02 - 4.17956065616942e-01 -8.77671504691748e-02 - 4.00609748442576e-01 -9.00880504606666e-02 - 3.83560931606009e-01 -9.19922123405806e-02 - 3.66843215733716e-01 -9.34852897893724e-02 - 3.50457316320503e-01 -9.45704569393238e-02 - 3.34434484008630e-01 -9.52913745446333e-02 - 3.18774100329315e-01 -9.56520593208299e-02 - 3.03499623121295e-01 -9.56762185217703e-02 - 2.88611293565648e-01 -9.54138023462325e-02 - 2.74124386665666e-01 -9.48530110497973e-02 - 2.60041455523719e-01 -9.40466437904150e-02 - 2.46374872015917e-01 -9.30158097462732e-02 - 2.33123443938834e-01 -9.17637361013487e-02 - 2.20293777810423e-01 -9.03241757366050e-02 - 2.07883282965331e-01 -8.87140409567101e-02 - 1.95902956391646e-01 -8.69458983005819e-02 - 1.84341253066628e-01 -8.50236979829755e-02 - 1.73213930954160e-01 -8.29816124281639e-02 - 1.62499176129638e-01 -8.08345589667689e-02 - 1.52214602777260e-01 -7.85858726432190e-02 - 1.42331759398971e-01 -7.62644966009465e-02 - 1.32872111539190e-01 -7.38926918573719e-02 - 1.23806439629760e-01 -7.14608957060230e-02 - 1.15147623386077e-01 -6.89962317568825e-02 - 1.06887208802748e-01 -6.64984409323291e-02 - 9.90071115215634e-02 -6.39771582792830e-02 - 9.15234043853439e-02 -6.14533554173981e-02 - 8.43970428172224e-02 -5.89269866114755e-02 - 7.76464790199521e-02 -5.64080271984127e-02 - 7.12479082120209e-02 -5.39056589365219e-02 - 6.51878662973747e-02 -5.14237900790153e-02 - 5.94874721274202e-02 -4.89818401558153e-02 - 5.41002464180900e-02 -4.65658443015086e-02 - 4.90378786701877e-02 -4.41823189959413e-02 - 4.43003497573338e-02 -4.18382382981486e-02 - 3.98423597346806e-02 -3.95268127030209e-02 - 3.56899752436130e-02 -3.72639820832858e-02 - 3.18292350050658e-02 -3.50553337728360e-02 - 2.82200072057899e-02 -3.28827269991516e-02 - 2.48925247792699e-02 -3.07683076116362e-02 - 2.18286683030034e-02 -2.87227694565966e-02 - 1.89846947131331e-02 -2.67116216483603e-02 - 1.63921917020335e-02 -2.47600239838931e-02 - 1.40446346341990e-02 -2.28973291396673e-02 - 1.18798249846349e-02 -2.10488243543874e-02 - 9.93094518736223e-03 -1.92230431144446e-02 - 8.21940795734749e-03 -1.75107128223999e-02 - 6.65838622137879e-03 -1.59102280398628e-02 - 5.26774192850643e-03 -1.43374059225501e-02 - 4.09515753852961e-03 -1.27402537516631e-02 - 3.09878859713640e-03 -1.10596206526992e-02 - 2.19660773551101e-03 -8.99028847950076e-03 - 1.46264176301869e-03 -6.42981938790989e-03 - 9.64484608297914e-04 -4.25962905981871e-03 - 5.99373867982851e-04 -2.59726247734802e-03 - 2.90086645599082e-04 -1.22886506907463e-03 - 7.80707788302466e-05 -3.21674666351397e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.43340407968326e-04 - 2.89878724192004e-04 1.30890254432191e-03 - 5.98775316682048e-04 2.90761974351082e-03 - 9.63326351634835e-04 5.00137520531067e-03 - 1.45966821282819e-03 7.62695714972799e-03 - 2.19097636449990e-03 1.05133029609055e-02 - 3.08997841959778e-03 1.28561752314486e-02 - 4.08271112470316e-03 1.49474073886688e-02 - 5.24853124383664e-03 1.70101541310158e-02 - 6.63128223001261e-03 1.91749271330955e-02 - 8.18368429859057e-03 2.14893648152745e-02 - 9.88361416849065e-03 2.37925422664720e-02 - 1.18176401547236e-02 2.61955200880562e-02 - 1.39661993216829e-02 2.86790220288215e-02 - 1.62951420791042e-02 3.12001193745238e-02 - 1.88631937781153e-02 3.37906348053943e-02 - 2.16807137532775e-02 3.64592283844348e-02 - 2.47159162958630e-02 3.91592631082371e-02 - 2.80064400105862e-02 4.19097431769445e-02 - 3.15762558914965e-02 4.47312559769947e-02 - 3.53948396168776e-02 4.75819141824782e-02 - 3.94949825480075e-02 5.04848832315002e-02 - 4.38979282781582e-02 5.34403146085306e-02 - 4.85758075737765e-02 5.64191271400408e-02 - 5.35679916138119e-02 5.94310594715804e-02 - 5.88818211488708e-02 6.24830291520826e-02 - 6.45001629027312e-02 6.55526503095466e-02 - 7.04692046391145e-02 6.86493092629647e-02 - 7.67740309924711e-02 7.17512569336527e-02 - 8.34162127168367e-02 7.48466808226862e-02 - 9.04290195190654e-02 7.79413995249654e-02 - 9.77906533229447e-02 8.10076632791090e-02 - 1.05536187198748e-01 8.40623495264620e-02 - 1.13658760041779e-01 8.70920309583710e-02 - 1.22161483318940e-01 9.00643366680361e-02 - 1.31067498602735e-01 9.29819011947911e-02 - 1.40354649921884e-01 9.58061506740306e-02 - 1.50055110786138e-01 9.85667892728282e-02 - 1.60148962661562e-01 1.01256666566183e-01 - 1.70658187899640e-01 1.03760241005947e-01 - 1.81574957422924e-01 1.06206694029936e-01 - 1.92907571409635e-01 1.08486778148673e-01 - 2.04657634577812e-01 1.10586586555802e-01 - 2.16817353069425e-01 1.12509327037815e-01 - 2.29396483963478e-01 1.14287527567059e-01 - 2.42377800694080e-01 1.15802131590720e-01 - 2.55773624268338e-01 1.17040720345952e-01 - 2.69566785632899e-01 1.18021545177475e-01 - 2.83765797226135e-01 1.18740230931095e-01 - 2.98347982887804e-01 1.19216919694706e-01 - 3.13318978785268e-01 1.19305990619727e-01 - 3.28658461892810e-01 1.19123871521493e-01 - 3.44364941645546e-01 1.18567426760901e-01 - 3.60419773725681e-01 1.17749032948798e-01 - 3.76811233766957e-01 1.16619067901022e-01 - 3.93525251020729e-01 1.15184881136724e-01 - 4.10538642553571e-01 1.13463604946276e-01 - 4.27843232490823e-01 1.11535561442414e-01 - 4.45406663468198e-01 1.09281922417313e-01 - 4.63222254103030e-01 1.06831909361838e-01 - 4.81251545655716e-01 1.04101415529277e-01 - 4.99481026671737e-01 1.01176032477657e-01 - 5.17879583085697e-01 9.81192291481330e-02 - 5.36417631367010e-01 9.48387402065250e-02 - 5.55075704909560e-01 9.14042779791586e-02 - 5.73808427242608e-01 8.78348043213490e-02 - 5.92596731105059e-01 8.41273691976704e-02 - 6.11401377553511e-01 8.03100957378549e-02 - 6.30186430605241e-01 7.63735423178241e-02 - 6.48926781663159e-01 7.24069753604002e-02 - 6.67570206424973e-01 6.83964362194056e-02 - 6.86088429590952e-01 6.43983729126918e-02 - 7.04445389043917e-01 6.03882571606010e-02 - 7.22592093722966e-01 5.64459089633876e-02 - 7.40501800453524e-01 5.25311344154134e-02 - 7.58125457122835e-01 4.87119646370781e-02 - 7.75421014376153e-01 4.49950074163821e-02 - 7.92362373587600e-01 4.13869901711966e-02 - 8.08894546151696e-01 3.79068656344119e-02 - 8.24974633014891e-01 3.45730000344855e-02 - 8.40576952273409e-01 3.13774270431009e-02 - 8.55652758808818e-01 2.83226330924249e-02 - 8.70162898882712e-01 2.54062499663936e-02 - 8.84085033071272e-01 2.26652310250962e-02 - 8.97361214262371e-01 2.00775083817710e-02 - 9.09954680076662e-01 1.76622385825581e-02 - 9.21851471402547e-01 1.54075337978015e-02 - 9.33012836658427e-01 1.33255713370600e-02 - 9.43389278969050e-01 1.14093490405974e-02 - 9.52973153850560e-01 9.67663586654917e-03 - 9.61743130827061e-01 8.10266937308276e-03 - 9.69640690675464e-01 6.69752021382239e-03 - 9.76664215898664e-01 5.45871719689547e-03 - 9.82815077112014e-01 4.38326629605338e-03 - 9.88028440045103e-01 3.47985730367389e-03 - 9.92304836603751e-01 2.74458959933797e-03 - 9.95693518775914e-01 2.16573541507002e-03 - 9.98120489340015e-01 1.75332792098647e-03 - 9.99443037908705e-01 1.52938027813976e-03 - 1.00000000000000e+00 1.43523280554541e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_37.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_37.dat index 37ab8b2e..788005f4 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_37.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_37.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_37_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF37_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF37_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.046729 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-13.965277 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.553763 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.143642 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.771269 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.135274 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006558 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079573 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006864 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079972 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -6.75362820507571e-03 2.34216786694829e-02 4.90046731986930e-03 --1.77714285740401e+02 5.78151286839241e-02 2.48962574701773e-02 9.14912499825966e-02 --1.75428571400002e+02 1.16380724827242e-01 2.57447081793811e-02 1.82668028108612e-01 --1.73142857116900e+02 1.68852300762506e-01 2.92475703463087e-02 2.74618546761004e-01 --1.70857160423602e+02 2.17693795863287e-01 3.82164218877117e-02 3.65347930215311e-01 --1.68571631778825e+02 2.65366335998713e-01 5.48007069864023e-02 3.92291331726918e-01 --1.66285714267592e+02 3.14345843179049e-01 7.85137241870269e-02 3.79325374419807e-01 --1.63999999984490e+02 3.67084130763597e-01 1.08197626271292e-01 3.66615875902270e-01 --1.61714472886699e+02 4.26044549647474e-01 1.42702421644669e-01 3.53917626344777e-01 --1.59428371284127e+02 4.92104626811618e-01 1.81032592142697e-01 3.48869174538751e-01 --1.57142842639350e+02 5.59656492437012e-01 2.22748636623105e-01 3.65478574356154e-01 --1.54857313994574e+02 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4.65696793097373e-18 2.40609865278164e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_37_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_37_Coords.txt deleted file mode 100644 index 7494714a..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_37_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.306324 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -4.71536408182645e-04 - 9.99429683992583e-01 -4.12546310012771e-04 - 9.98063017832965e-01 -2.72228791098884e-04 - 9.95573914266674e-01 -2.03715587530692e-05 - 9.92086309749559e-01 3.24638201223148e-04 - 9.87686148675057e-01 7.47117193517775e-04 - 9.82330525170640e-01 1.24318553194265e-03 - 9.76011908335692e-01 1.80447081766639e-03 - 9.68787467298381e-01 2.41659856781187e-03 - 9.60674860259240e-01 3.06931015930157e-03 - 9.51675358763677e-01 3.75486625124337e-03 - 9.41827652746244e-01 4.46392418320523e-03 - 9.31175295355131e-01 5.13341971102343e-03 - 9.19730397431178e-01 5.65608252047815e-03 - 9.07524559194720e-01 5.99605626724051e-03 - 8.94610408070308e-01 6.09870602534884e-03 - 8.81009696499435e-01 5.95719484093288e-03 - 8.66747905197194e-01 5.53262963657115e-03 - 8.51890258171205e-01 4.81415496678816e-03 - 8.36469462621421e-01 3.75393313042239e-03 - 8.20513485943698e-01 2.35391018196064e-03 - 8.04073832217581e-01 5.90340671765359e-04 - 7.87191529885653e-01 -1.56509537486666e-03 - 7.69897919101553e-01 -4.14433393504752e-03 - 7.52252341235159e-01 -7.09499240614545e-03 - 7.34291349178558e-01 -1.04195039254757e-02 - 7.16044924955764e-01 -1.41183071429631e-02 - 6.97571640033109e-01 -1.81647370850604e-02 - 6.78906186433687e-01 -2.25429063327247e-02 - 6.60080312620540e-01 -2.72141301070990e-02 - 6.41147517137212e-01 -3.21196337578167e-02 - 6.22137650968852e-01 -3.72119574064102e-02 - 6.03087998194415e-01 -4.24154104252760e-02 - 5.84045042118975e-01 -4.76826931812740e-02 - 5.65030897687003e-01 -5.28954952913379e-02 - 5.46088602779599e-01 -5.80099797612562e-02 - 5.27248673916899e-01 -6.29540849191656e-02 - 5.08535950506088e-01 -6.76949232599709e-02 - 4.89992355470388e-01 -7.21433010340976e-02 - 4.71632114506831e-01 -7.61958160395351e-02 - 4.53492503744347e-01 -7.98264621834988e-02 - 4.35593302897673e-01 -8.29992993450022e-02 - 4.17956065616942e-01 -8.57193691442574e-02 - 4.00609748442576e-01 -8.79863707091587e-02 - 3.83560931606009e-01 -8.98378160323954e-02 - 3.66843215733716e-01 -9.12848385312530e-02 - 3.50457316320503e-01 -9.23263158979776e-02 - 3.34434484008630e-01 -9.30097920780486e-02 - 3.18774100329315e-01 -9.33347141661698e-02 - 3.03499623121295e-01 -9.33291809544363e-02 - 2.88611293565648e-01 -9.30420367187734e-02 - 2.74124386665666e-01 -9.24644555504020e-02 - 2.60041455523719e-01 -9.16450388276567e-02 - 2.46374872015917e-01 -9.06106930109628e-02 - 2.33123443938834e-01 -8.93589869228667e-02 - 2.20293777810423e-01 -8.79259305887982e-02 - 2.07883282965331e-01 -8.63328701332691e-02 - 1.95902956391646e-01 -8.45857469868012e-02 - 1.84341253066628e-01 -8.26911107966286e-02 - 1.73213930954160e-01 -8.06808691439878e-02 - 1.62499176129638e-01 -7.85736895642996e-02 - 1.52214602777260e-01 -7.63688768254672e-02 - 1.42331759398971e-01 -7.40984116069325e-02 - 1.32872111539190e-01 -7.17820024187246e-02 - 1.23806439629760e-01 -6.94098832639032e-02 - 1.15147623386077e-01 -6.70100353396739e-02 - 1.06887208802748e-01 -6.45784322281852e-02 - 9.90071115215634e-02 -6.21270105621533e-02 - 9.15234043853439e-02 -5.96750032365549e-02 - 8.43970428172224e-02 -5.72206360806962e-02 - 7.76464790199521e-02 -5.47759319818528e-02 - 7.12479082120209e-02 -5.23471533225068e-02 - 6.51878662973747e-02 -4.99397380635475e-02 - 5.94874721274202e-02 -4.75736574827046e-02 - 5.41002464180900e-02 -4.52321476215274e-02 - 4.90378786701877e-02 -4.29204790407279e-02 - 4.43003497573338e-02 -4.06483970782307e-02 - 3.98423597346806e-02 -3.84079565749205e-02 - 3.56899752436130e-02 -3.62146273299273e-02 - 3.18292350050658e-02 -3.40734952164925e-02 - 2.82200072057899e-02 -3.19684351046893e-02 - 2.48925247792699e-02 -2.99174172734051e-02 - 2.18286683030034e-02 -2.79358464424135e-02 - 1.89846947131331e-02 -2.59831488911940e-02 - 1.63921917020335e-02 -2.40848125369980e-02 - 1.40446346341990e-02 -2.22866384664504e-02 - 1.18798249846349e-02 -2.05003293599271e-02 - 9.93094518736223e-03 -1.87266822788236e-02 - 8.21940795734749e-03 -1.70745391398301e-02 - 6.65838622137879e-03 -1.55548126321095e-02 - 5.26774192850643e-03 -1.40102185574345e-02 - 4.09515753852961e-03 -1.24191594956856e-02 - 3.09878859713640e-03 -1.07595226146166e-02 - 2.19660773551101e-03 -8.71369859550044e-03 - 1.46264176301869e-03 -6.15865893865364e-03 - 9.64484608297914e-04 -4.09759792012891e-03 - 5.99373867982851e-04 -2.52283455014017e-03 - 2.90086645599082e-04 -1.20192421632874e-03 - 7.80707788302466e-05 -3.17768671992027e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.28110197464213e-04 - 2.89878724192004e-04 1.27285242350633e-03 - 5.98775316682048e-04 2.79610127185876e-03 - 9.63326351634835e-04 4.72406314033313e-03 - 1.45966821282819e-03 7.24447148816348e-03 - 2.19097636449990e-03 1.01412102095474e-02 - 3.08997841959778e-03 1.24363871235525e-02 - 4.08271112470316e-03 1.45024779393962e-02 - 5.24853124383664e-03 1.65132342108356e-02 - 6.63128223001261e-03 1.86038066873273e-02 - 8.18368429859057e-03 2.08820533474607e-02 - 9.88361416849065e-03 2.31565313660361e-02 - 1.18176401547236e-02 2.55125506273496e-02 - 1.39661993216829e-02 2.79552662594453e-02 - 1.62951420791042e-02 3.04418476383060e-02 - 1.88631937781153e-02 3.29909874363904e-02 - 2.16807137532775e-02 3.56212551113666e-02 - 2.47159162958630e-02 3.82849995178998e-02 - 2.80064400105862e-02 4.10013748220475e-02 - 3.15762558914965e-02 4.37982009307693e-02 - 3.53948396168776e-02 4.66276006123415e-02 - 3.94949825480075e-02 4.95118721447292e-02 - 4.38979282781582e-02 5.24489048094132e-02 - 4.85758075737765e-02 5.54101587060903e-02 - 5.35679916138119e-02 5.84064114092154e-02 - 5.88818211488708e-02 6.14457287761441e-02 - 6.45001629027312e-02 6.45038544567554e-02 - 7.04692046391145e-02 6.75916131743311e-02 - 7.67740309924711e-02 7.06868309143716e-02 - 8.34162127168367e-02 7.37781839567767e-02 - 9.04290195190654e-02 7.68704060756461e-02 - 9.77906533229447e-02 7.99366525943175e-02 - 1.05536187198748e-01 8.29957658352020e-02 - 1.13658760041779e-01 8.60351355648582e-02 - 1.22161483318940e-01 8.90184043948807e-02 - 1.31067498602735e-01 9.19492617871951e-02 - 1.40354649921884e-01 9.47871530360260e-02 - 1.50055110786138e-01 9.75696820560994e-02 - 1.60148962661562e-01 1.00289053411997e-01 - 1.70658187899640e-01 1.02811644945142e-01 - 1.81574957422924e-01 1.05292893797589e-01 - 1.92907571409635e-01 1.07607520265941e-01 - 2.04657634577812e-01 1.09741721951514e-01 - 2.16817353069425e-01 1.11701453098982e-01 - 2.29396483963478e-01 1.13525785544796e-01 - 2.42377800694080e-01 1.15080245102572e-01 - 2.55773624268338e-01 1.16351595139648e-01 - 2.69566785632899e-01 1.17361780566947e-01 - 2.83765797226135e-01 1.18113282762572e-01 - 2.98347982887804e-01 1.18626259251996e-01 - 3.13318978785268e-01 1.18733231249748e-01 - 3.28658461892810e-01 1.18575221504911e-01 - 3.44364941645546e-01 1.18024872543305e-01 - 3.60419773725681e-01 1.17217046099090e-01 - 3.76811233766957e-01 1.16090986536980e-01 - 3.93525251020729e-01 1.14655476550547e-01 - 4.10538642553571e-01 1.12926055020483e-01 - 4.27843232490823e-01 1.10997768738798e-01 - 4.45406663468198e-01 1.08730096311341e-01 - 4.63222254103030e-01 1.06271811421282e-01 - 4.81251545655716e-01 1.03521217895113e-01 - 4.99481026671737e-01 1.00580759954275e-01 - 5.17879583085697e-01 9.75157235640591e-02 - 5.36417631367010e-01 9.42192015962077e-02 - 5.55075704909560e-01 9.07687112939123e-02 - 5.73808427242608e-01 8.71855134589316e-02 - 5.92596731105059e-01 8.34632450589685e-02 - 6.11401377553511e-01 7.96298721238774e-02 - 6.30186430605241e-01 7.56744584569126e-02 - 6.48926781663159e-01 7.16931720918476e-02 - 6.67570206424973e-01 6.76685523756470e-02 - 6.86088429590952e-01 6.36604623759597e-02 - 7.04445389043917e-01 5.96365631677187e-02 - 7.22592093722966e-01 5.56887264539795e-02 - 7.40501800453524e-01 5.17684936169993e-02 - 7.58125457122835e-01 4.79468696998886e-02 - 7.75421014376153e-01 4.42311817530751e-02 - 7.92362373587600e-01 4.06280034518494e-02 - 8.08894546151696e-01 3.71563338213875e-02 - 8.24974633014891e-01 3.38335275968718e-02 - 8.40576952273409e-01 3.06534652974441e-02 - 8.55652758808818e-01 2.76142410810304e-02 - 8.70162898882712e-01 2.47134637215999e-02 - 8.84085033071272e-01 2.19937559916790e-02 - 8.97361214262371e-01 1.94243737818370e-02 - 9.09954680076662e-01 1.70329044864875e-02 - 9.21851471402547e-01 1.47995718843507e-02 - 9.33012836658427e-01 1.27424649932607e-02 - 9.43389278969050e-01 1.08492414803022e-02 - 9.52973153850560e-01 9.14417530125850e-03 - 9.61743130827061e-01 7.59722087941313e-03 - 9.69640690675464e-01 6.21778555237072e-03 - 9.76664215898664e-01 5.00355108152492e-03 - 9.82815077112014e-01 3.95114739188035e-03 - 9.88028440045103e-01 3.06812658277290e-03 - 9.92304836603751e-01 2.35036694487206e-03 - 9.95693518775914e-01 1.78601979348168e-03 - 9.98120489340015e-01 1.38434179940443e-03 - 9.99443037908705e-01 1.16636444967019e-03 - 1.00000000000000e+00 1.07475752605493e-03 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_38.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_38.dat index 65a984c9..c4e87753 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_38.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_38.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_38_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF38_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF38_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-14.038094 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.768540 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.140093 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_38_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_38_Coords.txt deleted file mode 100644 index 1d259eaf..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_38_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.309305 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_39.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_39.dat index b5e0408b..5be80216 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_39.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_39.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_39_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF39_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF39_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-14.032107 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.767633 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.139467 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_39_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_39_Coords.txt deleted file mode 100644 index 6f7dfe95..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_39_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.313636 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_40.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_40.dat index 48aa65ae..6cba3134 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_40.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_40.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_40_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF40_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF40_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-14.026377 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.766760 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.138864 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_40_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_40_Coords.txt deleted file mode 100644 index 87b4162f..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_40_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.316799 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_41.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_41.dat index c7a0360f..980716dc 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_41.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_41.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_41_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF41_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF41_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-14.020856 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.765914 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.138279 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_41_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_41_Coords.txt deleted file mode 100644 index c4828707..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_41_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.320357 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_42.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_42.dat index 5ab0a31d..3e3a23ac 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_42.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_42.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_42_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF42_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF42_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-14.015514 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.765090 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.137710 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_42_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_42_Coords.txt deleted file mode 100644 index f7b7ec25..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_42_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.324414 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_43.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_43.dat index 1080f0af..5c4c32fb 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_43.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_43.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_43_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF43_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF43_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-14.010363 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.764291 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.137158 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_43_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_43_Coords.txt deleted file mode 100644 index 6266e080..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_43_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.328813 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_44.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_44.dat index 0f20b6f0..801fe7d8 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_44.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_44.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_44_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF44_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF44_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-14.005395 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.763517 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.136623 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_44_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_44_Coords.txt deleted file mode 100644 index 14256e68..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_44_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.333523 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_45.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_45.dat index fe466682..04c4d891 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_45.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_45.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_45_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF45_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF45_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-14.000601 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.762765 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.136104 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_45_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_45_Coords.txt deleted file mode 100644 index 7730e95e..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_45_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.338467 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_46.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_46.dat index f969d447..b4770b9b 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_46.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_46.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_46_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF46_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF46_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-13.995972 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.762036 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.135601 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_46_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_46_Coords.txt deleted file mode 100644 index f20d011a..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_46_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.343745 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_47.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_47.dat index 8899803b..f3a57ee9 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_47.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_47.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_47_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF47_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF47_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-13.991505 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.761329 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.135112 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_47_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_47_Coords.txt deleted file mode 100644 index 60aee7e6..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_47_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.349500 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_48.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_48.dat index 32ad5fbf..14743c82 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_48.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_48.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_48_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF48_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF48_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-13.987158 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.760638 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.134635 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_48_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_48_Coords.txt deleted file mode 100644 index 9925d64d..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_48_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.358268 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_49.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_49.dat index e888e67c..933d65d4 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_49.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_49.dat @@ -5,21 +5,21 @@ ! ------------------------------------------------------------------------------ DEFAULT InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"IEA-15-240-RWT_AeroDyn15_Polar_49_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +@"IEA-15-240-RWT_AF49_Coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. AF49_BL.txt BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. 1 NumTabs ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. ! ------------------------------------------------------------------------------ -! data for table 1 +! data for table 1 ! ------------------------------------------------------------------------------ - 0.750000 Re ! Reynolds number in millions -0 UserProp ! User property (control) setting +3.000000 Re ! Reynolds number in millions +0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line !........................................ - -3.058069 alpha0 ! 0-lift angle of attack, depends on airfoil. - 13.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) - -13.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOAalpha0. (deg) +-13.951621 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] - 0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] - 0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] - 1.549456 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. - -1.146560 Cn2 ! As Cn1 for negative AOAs. +0.000000 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.754861 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.130644 Cn2 ! As Cn1 for negative AOAs. Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] - 0.006566 Cd0 ! 2D drag coefficient value at 0-lift. - -0.079233 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] - 0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] - 0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] - 0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +0.006831 Cd0 ! 2D drag coefficient value at 0-lift. +-0.079741 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] !........................................ ! Table of aerodynamics coefficients -120 NumAlf ! Number of data lines in the following table +200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm ! (deg) (-) (-) (-) --1.80000000000000e+02 -8.05341794396480e-03 2.41346188032050e-02 4.89921703324773e-03 --1.77714285740401e+02 5.76539531761537e-02 2.54999535477012e-02 9.14875573243886e-02 --1.75428571400002e+02 1.16060686104043e-01 2.64054961683649e-02 1.82680233296262e-01 --1.73142857116900e+02 1.68390943822971e-01 3.01200691531336e-02 2.74593999731515e-01 --1.70857160423602e+02 2.17100823740126e-01 3.93301069273706e-02 3.65378890802789e-01 --1.68571631778825e+02 2.64643642039723e-01 5.60838164635009e-02 3.92134370524925e-01 --1.66285714267592e+02 3.13487505794451e-01 7.98889365807728e-02 3.78918792348635e-01 --1.63999999984490e+02 3.66076499624477e-01 1.09605908734732e-01 3.66069411685130e-01 --1.61714472886699e+02 4.24866199102630e-01 1.44099365157748e-01 3.53039283084089e-01 --1.59428371284127e+02 4.90732128874889e-01 1.82391790507777e-01 3.47865620286872e-01 --1.57142842639350e+02 5.58088109806376e-01 2.24050684247759e-01 3.64432134438547e-01 --1.54857313994574e+02 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4.85722573273506e-18 2.46414625588597e-02 0.00000000000000e+00 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_49_Coords.txt b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_49_Coords.txt deleted file mode 100644 index 44374d93..00000000 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_49_Coords.txt +++ /dev/null @@ -1,208 +0,0 @@ - 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. -! ......... x-y coordinates are next if NumCoords > 0 ............. -! x-y coordinate of airfoil reference -! x/c y/c - 0.368182 0. -! coordinates of airfoil shape -! interpolation to 200 points -! x/c y/c - 1.00000000000000e+00 -3.70000000000000e-04 - 9.99429683992583e-01 -3.12530401102541e-04 - 9.98063017832965e-01 -1.75779784519388e-04 - 9.95573914266674e-01 6.98595831962172e-05 - 9.92086309749559e-01 4.06750023865230e-04 - 9.87686148675057e-01 8.20030122370873e-04 - 9.82330525170640e-01 1.30603042959075e-03 - 9.76011908335692e-01 1.85661014175110e-03 - 9.68787467298381e-01 2.45775021921419e-03 - 9.60674860259240e-01 3.09944998003919e-03 - 9.51675358763677e-01 3.77384009009967e-03 - 9.41827652746244e-01 4.47174981783311e-03 - 9.31175295355131e-01 5.13478024507654e-03 - 9.19730397431178e-01 5.65716008906736e-03 - 9.07524559194720e-01 5.99693001000373e-03 - 8.94610408070308e-01 6.09949000000000e-03 - 8.81009696499435e-01 5.95798994623460e-03 - 8.66747905197194e-01 5.53357982335698e-03 - 8.51890258171205e-01 4.81535989631074e-03 - 8.36469462621421e-01 3.75549020188999e-03 - 8.20513485943698e-01 2.35598960878764e-03 - 8.04073832217581e-01 5.93130258126354e-04 - 7.87191529885653e-01 -1.55747001564946e-03 - 7.69897919101553e-01 -4.11605014036506e-03 - 7.52252341235159e-01 -7.03745978530337e-03 - 7.34291349178558e-01 -1.03244301571225e-02 - 7.16044924955764e-01 -1.39806389686777e-02 - 6.97571640033109e-01 -1.79798699925875e-02 - 6.78906186433687e-01 -2.23071208500927e-02 - 6.60080312620540e-01 -2.69251493431809e-02 - 6.41147517137212e-01 -3.17763307459790e-02 - 6.22137650968852e-01 -3.68154697405875e-02 - 6.03087998194415e-01 -4.19680404916622e-02 - 5.84045042118975e-01 -4.71885694215656e-02 - 5.65030897687003e-01 -5.23570406241553e-02 - 5.46088602779599e-01 -5.74317292657191e-02 - 5.27248673916899e-01 -6.23403289969140e-02 - 5.08535950506088e-01 -6.70521998760328e-02 - 4.89992355470388e-01 -7.14745710351050e-02 - 4.71632114506831e-01 -7.55024890597704e-02 - 4.53492503744347e-01 -7.91105893007070e-02 - 4.35593302897673e-01 -8.22618395256941e-02 - 4.17956065616942e-01 -8.49601306147296e-02 - 4.00609748442576e-01 -8.72069501828722e-02 - 3.83560931606009e-01 -8.90385898471080e-02 - 3.66843215733716e-01 -9.04683503081238e-02 - 3.50457316320503e-01 -9.14934301842080e-02 - 3.34434484008630e-01 -9.21628698921142e-02 - 3.18774100329315e-01 -9.24743500000000e-02 - 3.03499623121295e-01 -9.24576600064911e-02 - 2.88611293565648e-01 -9.21612000951899e-02 - 2.74124386665666e-01 -9.15773298406870e-02 - 2.60041455523719e-01 -9.07529697041433e-02 - 2.46374872015917e-01 -8.97172901696196e-02 - 2.33123443938834e-01 -8.84656804030273e-02 - 2.20293777810423e-01 -8.70349897390697e-02 - 2.07883282965331e-01 -8.54483204033298e-02 - 1.95902956391646e-01 -8.37090194456859e-02 - 1.84341253066628e-01 -8.18246605242051e-02 - 1.73213930954160e-01 -7.98262601785762e-02 - 1.62499176129638e-01 -7.77339492115459e-02 - 1.52214602777260e-01 -7.55454906112649e-02 - 1.42331759398971e-01 -7.32940298587153e-02 - 1.32872111539190e-01 -7.09982703859269e-02 - 1.23806439629760e-01 -6.86484099012840e-02 - 1.15147623386077e-01 -6.62727409571903e-02 - 1.06887208802748e-01 -6.38657996415142e-02 - 9.90071115215634e-02 -6.14404204804907e-02 - 9.15234043853439e-02 -5.90151814568963e-02 - 8.43970428172224e-02 -5.65876009838068e-02 - 7.76464790199521e-02 -5.41705496407600e-02 - 7.12479082120209e-02 -5.17691193136248e-02 - 6.51878662973747e-02 -4.93893685140959e-02 - 5.94874721274202e-02 -4.70514808928498e-02 - 5.41002464180900e-02 -4.47376084229382e-02 - 4.90378786701877e-02 -4.24525793849528e-02 - 4.43003497573338e-02 -4.02072798822726e-02 - 3.98423597346806e-02 -3.79932398649127e-02 - 3.56899752436130e-02 -3.58257574559120e-02 - 3.18292350050658e-02 -3.37097171928781e-02 - 2.82200072057899e-02 -3.16297683442471e-02 - 2.48925247792699e-02 -2.96022729823280e-02 - 2.18286683030034e-02 -2.76444488822720e-02 - 1.89846947131331e-02 -2.57133533060338e-02 - 1.63921917020335e-02 -2.38346412597173e-02 - 1.40446346341990e-02 -2.20605536350075e-02 - 1.18798249846349e-02 -2.02973942665553e-02 - 9.93094518736223e-03 -1.85429955433051e-02 - 8.21940795734749e-03 -1.69132580530240e-02 - 6.65838622137879e-03 -1.54239061274413e-02 - 5.26774192850643e-03 -1.38891423533249e-02 - 4.09515753852961e-03 -1.22995063181749e-02 - 3.09878859713640e-03 -1.06474073109417e-02 - 2.19660773551101e-03 -8.61061375439793e-03 - 1.46264176301869e-03 -6.05796663005623e-03 - 9.64484608297914e-04 -4.04021906681413e-03 - 5.99373867982851e-04 -2.49969631815273e-03 - 2.90086645599082e-04 -1.19504599223452e-03 - 7.80707788302466e-05 -3.17453190720864e-04 - 0.00000000000000e+00 0.00000000000000e+00 - 7.80412061165972e-05 3.22675135603479e-04 - 2.89878724192004e-04 1.26290410504709e-03 - 5.98775316682048e-04 2.75973672528357e-03 - 9.63326351634835e-04 4.62178156211258e-03 - 1.45966821282819e-03 7.10111203944765e-03 - 2.19097636449990e-03 1.00016486746841e-02 - 3.08997841959778e-03 1.22788963916458e-02 - 4.08271112470316e-03 1.43357621114091e-02 - 5.24853124383664e-03 1.63270419846742e-02 - 6.63128223001261e-03 1.83896532901645e-02 - 8.18368429859057e-03 2.06543959895304e-02 - 9.88361416849065e-03 2.29182752888995e-02 - 1.18176401547236e-02 2.52567101808432e-02 - 1.39661993216829e-02 2.76842092569614e-02 - 1.62951420791042e-02 3.01579721282135e-02 - 1.88631937781153e-02 3.26916536160595e-02 - 2.16807137532775e-02 3.53076233790975e-02 - 2.47159162958630e-02 3.79578368627121e-02 - 2.80064400105862e-02 4.06615000084802e-02 - 3.15762558914965e-02 4.34493168791364e-02 - 3.53948396168776e-02 4.62711297240942e-02 - 3.94949825480075e-02 4.91488117414431e-02 - 4.38979282781582e-02 5.20793588835992e-02 - 4.85758075737765e-02 5.50344085075244e-02 - 5.35679916138119e-02 5.80251809439684e-02 - 5.88818211488708e-02 6.10601606401137e-02 - 6.45001629027312e-02 6.41143615384598e-02 - 7.04692046391145e-02 6.71991823356800e-02 - 7.67740309924711e-02 7.02922704740952e-02 - 8.34162127168367e-02 7.33825112302781e-02 - 9.04290195190654e-02 7.64741797939341e-02 - 9.77906533229447e-02 7.95408213481325e-02 - 1.05536187198748e-01 8.26019989221880e-02 - 1.13658760041779e-01 8.56454300151557e-02 - 1.22161483318940e-01 8.86332211293666e-02 - 1.31067498602735e-01 9.15694495562681e-02 - 1.40354649921884e-01 9.44127999768207e-02 - 1.50055110786138e-01 9.72039602192805e-02 - 1.60148962661562e-01 9.99348306783638e-02 - 1.70658187899640e-01 1.02464809507446e-01 - 1.81574957422924e-01 1.04959519442250e-01 - 1.92907571409635e-01 1.07287470272758e-01 - 2.04657634577812e-01 1.09434880787374e-01 - 2.16817353069425e-01 1.11408780472748e-01 - 2.29396483963478e-01 1.13250800525266e-01 - 2.42377800694080e-01 1.14820510074261e-01 - 2.55773624268338e-01 1.16104320356806e-01 - 2.69566785632899e-01 1.17125599727623e-01 - 2.83765797226135e-01 1.17889589879986e-01 - 2.98347982887804e-01 1.18416390036325e-01 - 3.13318978785268e-01 1.18530000000000e-01 - 3.28658461892810e-01 1.18381139971318e-01 - 3.44364941645546e-01 1.17832859932348e-01 - 3.60419773725681e-01 1.17028869784395e-01 - 3.76811233766957e-01 1.15904059712656e-01 - 3.93525251020729e-01 1.14467769904873e-01 - 4.10538642553571e-01 1.12734889728239e-01 - 4.27843232490823e-01 1.10806239701716e-01 - 4.45406663468198e-01 1.08532819536450e-01 - 4.63222254103030e-01 1.06071059404224e-01 - 4.81251545655716e-01 1.03312350682916e-01 - 4.99481026671737e-01 1.00365790546381e-01 - 5.17879583085697e-01 9.72972894683925e-02 - 5.36417631367010e-01 9.39942997516781e-02 - 5.55075704909560e-01 9.05373390751697e-02 - 5.73808427242608e-01 8.69485905375338e-02 - 5.92596731105059e-01 8.32203697775818e-02 - 6.11401377553511e-01 7.93805405077047e-02 - 6.30186430605241e-01 7.54176298717753e-02 - 6.48926781663159e-01 7.14304296433249e-02 - 6.67570206424973e-01 6.74001507737061e-02 - 6.86088429590952e-01 6.33879500892043e-02 - 7.04445389043917e-01 5.93584602089902e-02 - 7.22592093722966e-01 5.54082191870821e-02 - 7.40501800453524e-01 5.14855999011489e-02 - 7.58125457122835e-01 4.76627106210760e-02 - 7.75421014376153e-01 4.39471690648101e-02 - 7.92362373587600e-01 4.03455092423240e-02 - 8.08894546151696e-01 3.68767308007861e-02 - 8.24974633014891e-01 3.35577993822112e-02 - 8.40576952273409e-01 3.03833395400220e-02 - 8.55652758808818e-01 2.73497302386713e-02 - 8.70162898882712e-01 2.44546002202302e-02 - 8.84085033071272e-01 2.17427394044904e-02 - 8.97361214262371e-01 1.91800691855632e-02 - 9.09954680076662e-01 1.67974299855790e-02 - 9.21851471402547e-01 1.45719997402033e-02 - 9.33012836658427e-01 1.25241606099569e-02 - 9.43389278969050e-01 1.06395101847093e-02 - 9.52973153850560e-01 8.94480932223594e-03 - 9.61743130827061e-01 7.40798985582653e-03 - 9.69640690675464e-01 6.03819988349410e-03 - 9.76664215898664e-01 4.83319069969999e-03 - 9.82815077112014e-01 3.78945048740357e-03 - 9.88028440045103e-01 2.91408999246443e-03 - 9.92304836603751e-01 2.20291056237329e-03 - 9.95693518775914e-01 1.64402020118296e-03 - 9.98120489340015e-01 1.24638010786988e-03 - 9.99443037908705e-01 1.03065034069941e-03 - 1.00000000000000e+00 9.40000000000000e-04 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi.fst b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi.fst index a2684323..4e86355e 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi.fst +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi.fst @@ -27,7 +27,7 @@ False Echo - Echo input data to .ech (flag) 335 SpdSound - Speed of sound in working fluid (m/s) 103500 Patm - Atmospheric pressure (Pa) [used only for an MHK turbine cavitation check] 1700 Pvap - Vapour pressure of working fluid (Pa) [used only for an MHK turbine cavitation check] - 50 WtrDpth - Water depth (m) + 200 WtrDpth - Water depth (m) 0 MSL2SWL - Offset between still-water level and mean sea level (m) [positive upward] ---------------------- INPUT FILES --------------------------------------------- "IEA-15-240-RWT-UMaineSemi_ElastoDyn.dat" EDFile - Name of file containing ElastoDyn input parameters (quoted string) diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ElastoDyn.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ElastoDyn.dat index c0f6fbe7..eb29f737 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ElastoDyn.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ElastoDyn.dat @@ -42,8 +42,8 @@ True PtfmYDOF - Platform yaw rotation DOF (flag) 0 PtfmYaw - Initial or fixed yaw rotational displacement of platform (degrees) ---------------------- TURBINE CONFIGURATION ----------------------------------- 3 NumBl - Number of blades (-) - 120 TipRad - The distance from the rotor apex to the blade tip (meters) - 3 HubRad - The distance from the rotor apex to the blade root (meters) + 120.97 TipRad - The distance from the rotor apex to the blade tip (meters) + 3.97 HubRad - The distance from the rotor apex to the blade root (meters) -4 PreCone(1) - Blade 1 cone angle (degrees) -4 PreCone(2) - Blade 2 cone angle (degrees) -4 PreCone(3) - Blade 3 cone angle (degrees) [unused for 2 blades] @@ -51,38 +51,38 @@ True PtfmYDOF - Platform yaw rotation DOF (flag) 0 UndSling - Undersling length [distance from teeter pin to the rotor apex] (meters) [unused for 3 blades] 0 Delta3 - Delta-3 angle for teetering rotors (degrees) [unused for 3 blades] 0 AzimB1Up - Azimuth value to use for I/O when blade 1 points up (degrees) - -11.075 OverHang - Distance from yaw axis to rotor apex [3 blades] or teeter pin [2 blades] (meters) - 0 ShftGagL - Distance from rotor apex [3 blades] or teeter pin [2 blades] to shaft strain gages [positive for upwind rotors] (meters) - -6 ShftTilt - Rotor shaft tilt angle (degrees) - -4.985 NacCMxn - Downwind distance from the tower-top to the nacelle CM (meters) - 0 NacCMyn - Lateral distance from the tower-top to the nacelle CM (meters) - 4.358 NacCMzn - Vertical distance from the tower-top to the nacelle CM (meters) - -4.985 NcIMUxn - Downwind distance from the tower-top to the nacelle IMU (meters) - 0 NcIMUyn - Lateral distance from the tower-top to the nacelle IMU (meters) - 4.358 NcIMUzn - Vertical distance from the tower-top to the nacelle IMU (meters) - 4.3478 Twr2Shft - Vertical distance from the tower-top to the rotor shaft (meters) - 144.495 TowerHt - Height of tower above ground level [onshore] or MSL [offshore] (meters) + -12.098 OverHang - Distance from yaw axis to rotor apex [3 blades] or teeter pin [2 blades] (meters) + 0.0 ShftGagL - Distance from rotor apex [3 blades] or teeter pin [2 blades] to shaft strain gages [positive for upwind rotors] (meters) + -6.0 ShftTilt - Rotor shaft tilt angle (degrees) + -5.125 NacCMxn - Downwind distance from the tower-top to the nacelle CM (meters) + 0.0 NacCMyn - Lateral distance from the tower-top to the nacelle CM (meters) + 4.315 NacCMzn - Vertical distance from the tower-top to the nacelle CM (meters) + 0.0 NcIMUxn - Downwind distance from the tower-top to the nacelle IMU (meters) + 0.0 NcIMUyn - Lateral distance from the tower-top to the nacelle IMU (meters) + 0.0 NcIMUzn - Vertical distance from the tower-top to the nacelle IMU (meters) + 4.3495 Twr2Shft - Vertical distance from the tower-top to the rotor shaft (meters) + 144.386 TowerHt - Height of tower above ground level [onshore] or MSL [offshore] (meters) 15 TowerBsHt - Height of tower base above ground level [onshore] or MSL [offshore] (meters) 0 PtfmCMxt - Downwind distance from the ground level [onshore] or MSL [offshore] to the platform CM (meters) 0 PtfmCMyt - Lateral distance from the ground level [onshore] or MSL [offshore] to the platform CM (meters) - -14.94 PtfmCMzt - Vertical distance from the ground level [onshore] or MSL [offshore] to the platform CM (meters) + -14.400 PtfmCMzt - Vertical distance from the ground level [onshore] or MSL [offshore] to the platform CM (meters) 0 PtfmRefzt - Vertical distance from the ground level [onshore] or MSL [offshore] to the platform reference point (meters) ---------------------- MASS AND INERTIA ---------------------------------------- 0 TipMass(1) - Tip-brake mass, blade 1 (kg) 0 TipMass(2) - Tip-brake mass, blade 2 (kg) 0 TipMass(3) - Tip-brake mass, blade 3 (kg) [unused for 2 blades] - 190000 HubMass - Hub mass (kg) -1.37347E+06 HubIner - Hub inertia about rotor axis [3 blades] or teeter axis [2 blades] (kg m^2) -8.00865E+06 GenIner - Generator inertia about HSS (kg m^2) - 507275 NacMass - Nacelle mass (kg) -1.96179E+07 NacYIner - Nacelle inertia about yaw axis (kg m^2) - 100000 YawBrMass - Yaw bearing mass (kg) + 69131 HubMass - Hub mass (kg) + 969952 HubIner - Hub inertia about rotor axis [3 blades] or teeter axis [2 blades] (kg m^2) + 1836784 GenIner - Generator inertia about HSS (kg m^2) + 644857 NacMass - Nacelle mass (kg) + 32929058 NacYIner - Nacelle inertia about yaw axis (kg m^2) + 28249 YawBrMass - Yaw bearing mass (kg) 1.7838E+07 PtfmMass - Platform mass (kg) 1.2507E+10 PtfmRIner - Platform inertia for roll tilt rotation about the platform CM (kg m^2) 1.2507E+10 PtfmPIner - Platform inertia for pitch tilt rotation about the platform CM (kg m^2) 2.3667E+10 PtfmYIner - Platform inertia for yaw rotation about the platform CM (kg m^2) ---------------------- BLADE --------------------------------------------------- - 20 BldNodes - Number of blade nodes (per blade) used for analysis (-) + 50 BldNodes - Number of blade nodes (per blade) used for analysis (-) "IEA-15-240-RWT_ElastoDyn_blade.dat" BldFile1 - Name of file containing properties for blade 1 (quoted string) "IEA-15-240-RWT_ElastoDyn_blade.dat" BldFile2 - Name of file containing properties for blade 2 (quoted string) "IEA-15-240-RWT_ElastoDyn_blade.dat" BldFile3 - Name of file containing properties for blade 3 (quoted string) [unused for 2 blades] @@ -98,13 +98,13 @@ True PtfmYDOF - Platform yaw rotation DOF (flag) ---------------------- DRIVETRAIN ---------------------------------------------- 100 GBoxEff - Gearbox efficiency (%) 1 GBRatio - Gearbox ratio (-) - 8.235E+11 DTTorSpr - Drivetrain torsional spring (N-m/rad) - 6.215E+06 DTTorDmp - Drivetrain torsional damper (N-m/(rad/s)) +69737644900 DTTorSpr - Drivetrain torsional spring (N-m/rad) + 49418406 DTTorDmp - Drivetrain torsional damper (N-m/(rad/s)) ---------------------- FURLING ------------------------------------------------- False Furling - Read in additional model properties for furling turbine (flag) [must currently be FALSE) "unused" FurlFile - Name of file containing furling properties (quoted string) [unused when Furling=False] ---------------------- TOWER --------------------------------------------------- - 50 TwrNodes - Number of tower nodes used for analysis (-) + 20 TwrNodes - Number of tower nodes used for analysis (-) "IEA-15-240-RWT-UMaineSemi_ElastoDyn_tower.dat" TwrFile - Name of file containing tower properties (quoted string) ---------------------- OUTPUT -------------------------------------------------- True SumPrint - Print summary data to ".sum" (flag) diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_HydroDyn.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_HydroDyn.dat index fa88672b..0c44f390 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_HydroDyn.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_HydroDyn.dat @@ -2,17 +2,17 @@ IEA 15 MW offshore reference model on UMaine VolturnUS-S semi-submersible floating platform False Echo - Echo the input file data (flag) ---------------------- ENVIRONMENTAL CONDITIONS -------------------------------- - 1025 WtrDens - Water density (kg/m^3) - 200 WtrDpth - Water depth (meters) - 0 MSL2SWL - Offset between still-water level and mean sea level (meters) [positive upward; unused when WaveMod = 6; must be zero if PotMod=1 or 2] + "default" WtrDens - Water density (kg/m^3) + "default" WtrDpth - Water depth (meters) + "default" MSL2SWL - Offset between still-water level and mean sea level (meters) [positive upward; unused when WaveMod = 6; must be zero if PotMod=1 or 2] ---------------------- WAVES --------------------------------------------------- - 0 WaveMod - Incident wave kinematics model {0: none=still water, 1: plane progressive (regular), 2: JONSWAP/Pierson-Moskowitz spectrum (irregular), 3: user-defind spectrum from routine UserWaveSpctrm (irregular)} (switch) + 2 WaveMod - Incident wave kinematics model {0: none=still water, 1: regular (periodic), 1P#: regular with user-specified phase, 2: JONSWAP/Pierson-Moskowitz spectrum (irregular), 3: White noise spectrum (irregular), 4: user-defined spectrum from routine UserWaveSpctrm (irregular), 5: Externally generated wave-elevation time series, 6: Externally generated full wave-kinematics time series [option 6 is invalid for PotMod/=0]} (switch) 0 WaveStMod - Model for stretching incident wave kinematics to instantaneous free surface {0: none=no stretching, 1: vertical stretching, 2: extrapolation stretching, 3: Wheeler stretching} (switch) [unused when WaveMod=0 or when PotMod/=0] 850.00 WaveTMax - Analysis time for incident wave calculations (sec) [unused when WaveMod=0; determines WaveDOmega=2Pi/WaveTMax in the IFFT] 0.25 WaveDT - Time step for incident wave calculations (sec) [unused when WaveMod=0; 0.1<=WaveDT<=1.0 recommended; determines WaveOmegaMax=Pi/WaveDT in the IFFT] - 1.10 WaveHs - Significant wave height of incident waves (meters) [used only when WaveMod=1 or 2] - 8.52 WaveTp - Peak spectral period of incident waves (sec) [used only when WaveMod=1 or 2] - 1.00 WavePkShp - Peak-shape parameter of incident wave spectrum (-) or DEFAULT (string) [used only when WaveMod=2; use 1.0 for Pierson-Moskowitz] + 1.10 WaveHs - Significant wave height of incident waves (meters) [used only when WaveMod=1 or 2] + 8.52 WaveTp - Peak spectral period of incident waves (sec) [used only when WaveMod=1 or 2] + DEFAULT WavePkShp - Peak-shape parameter of incident wave spectrum (-) or DEFAULT (string) [used only when WaveMod=2; use 1.0 for Pierson-Moskowitz] 0.111527 WvLowCOff - Low cut-off frequency or lower frequency limit of the wave spectrum beyond which the wave spectrum is zeroed (rad/s) [unused when WaveMod=0, 1, or 6] 0.783827 WvHiCOff - High cut-off frequency or upper frequency limit of the wave spectrum beyond which the wave spectrum is zeroed (rad/s) [unused when WaveMod=0, 1, or 6] 0.00 WaveDir - Incident wave propagation heading direction (degrees) [unused when WaveMod=0 or 6] @@ -29,7 +29,7 @@ False Echo - Echo the input file data (flag) 0 WaveElevyi - List of yi-coordinates for points where the incident wave elevations can be output (meters) [NWaveElev points, separated by commas or white space; usused if NWaveElev = 0] ---------------------- 2ND-ORDER WAVES ----------------------------------------- [unused with WaveMod=0 or 6] True WvDiffQTF - Full difference-frequency 2nd-order wave kinematics (flag) - False WvSumQTF - Full summation-frequency 2nd-order wave kinematics (flag) + True WvSumQTF - Full summation-frequency 2nd-order wave kinematics (flag) 0 WvLowCOffD - Low frequency cutoff used in the difference-frequencies (rad/s) [Only used with a difference-frequency method] 0.737863 WvHiCOffD - High frequency cutoff used in the difference-frequencies (rad/s) [Only used with a difference-frequency method] 0.314159 WvLowCOffS - Low frequency cutoff used in the summation-frequencies (rad/s) [Only used with a summation-frequency method] @@ -45,12 +45,12 @@ False Echo - Echo the input file data (flag) 0 CurrDIDir - Depth-independent current heading direction (degrees) [used only when CurrMod=1] ---------------------- FLOATING PLATFORM --------------------------------------- [unused with WaveMod=6] 1 PotMod - Potential-flow model {0: none=no potential flow, 1: frequency-to-time-domain transforms based on WAMIT output, 2: fluid-impulse theory (FIT)} (switch) - 1 ExctnMod - Wave-excitation model {0: no wave-excitation calculation, 1: DFT, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ssexctn INPUT FILE] - 1 RdtnMod - Radiation memory-effect model {0: no memory-effect calculation, 1: convolution, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ss INPUT FILE] - 60 RdtnTMax - Analysis time for wave radiation kernel calculations (sec) [only used when PotMod=1; determines RdtnDOmega=Pi/RdtnTMax in the cosine transform; MAKE SURE THIS IS LONG ENOUGH FOR THE RADIATION IMPULSE RESPONSE FUNCTIONS TO DECAY TO NEAR-ZERO FOR THE GIVEN PLATFORM!] - "DEFAULT" RdtnDT - Time step for wave radiation kernel calculations (sec) [only used when PotMod=1; DT<=RdtnDT<=0.1 recommended; determines RdtnOmegaMax=Pi/RdtnDT in the cosine transform] - 1 NBody - Number of WAMIT bodies to be used (-) [>=1; only used when PotMod=1. If NBodyMod=1, the WAMIT data contains a vector of size 6*NBody x 1 and matrices of size 6*NBody x 6*NBody; if NBodyMod>1, there are NBody sets of WAMIT data each with a vector of size 6 x 1 and matrices of size 6 x 6] - 1 NBodyMod - Body coupling model {1: include coupling terms between each body and NBody in HydroDyn equals NBODY in WAMIT, 2: neglect coupling terms between each body and NBODY=1 with XBODY=0 in WAMIT, 3: Neglect coupling terms between each body and NBODY=1 with XBODY=/0 in WAMIT} (switch) [only used when PotMod=1] + 1 ExctnMod - Wave Excitation model {0: None, 1: DFT, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ssexctn INPUT FILE] + 1 RdtnMod - Radiation memory-effect model {0: no memory-effect calculation, 1: convolution, 2: state-space} (switch) [only used when PotMod=1; STATE-SPACE REQUIRES *.ss INPUT FILE] + 60.0 RdtnTMax - Analysis time for wave radiation kernel calculations (sec) [only used when PotMod=1; determines RdtnDOmega=Pi/RdtnTMax in the cosine transform; MAKE SURE THIS IS LONG ENOUGH FOR THE RADIATION IMPULSE RESPONSE FUNCTIONS TO DECAY TO NEAR-ZERO FOR THE GIVEN PLATFORM!] + "DEFAULT" RdtnDT - Time step for wave radiation kernel calculations (sec) [only used when PotMod=1; DT<=RdtnDT<=0.1 recommended; determines RdtnOmegaMax=Pi/RdtnDT in the cosine transform] + 1 NBody - Number of WAMIT bodies to be used (-) [>=1; only used when PotMod=1. If NBodyMod=1, the WAMIT data contains a vector of size 6*NBody x 1 and matrices of size 6*NBody x 6*NBody; if NBodyMod>1, there are NBody sets of WAMIT data each with a vector of size 6 x 1 and matrices of size 6 x 6] + 1 NBodyMod - Body coupling model {1: include coupling terms between each body and NBody in HydroDyn equals NBODY in WAMIT, 2: neglect coupling terms between each body and NBODY=1 with XBODY=0 in WAMIT, 3: Neglect coupling terms between each body and NBODY=1 with XBODY=/0 in WAMIT} (switch) [only used when PotMod=1] "HydroData/IEA-15-240-RWT-UMaineSemi" PotFile - Root name of potential-flow model data; WAMIT output files containing the linear, nondimensionalized, hydrostatic restoring matrix (.hst), frequency-dependent hydrodynamic added mass matrix and damping matrix (.1), and frequency- and direction-dependent wave excitation force vector per unit wave amplitude (.3) (quoted string) [MAKE SURE THE FREQUENCIES INHERENT IN THESE WAMIT FILES SPAN THE PHYSICALLY-SIGNIFICANT RANGE OF FREQUENCIES FOR THE GIVEN PLATFORM; THEY MUST CONTAIN THE ZERO- AND INFINITE-FREQUENCY LIMITS!] 1 WAMITULEN - Characteristic body length scale used to redimensionalize WAMIT output (meters) [only used when PotMod=1] 0.0 PtfmRefxt - The xt offset of the body reference point(s) from (0,0,0) (meters) [1 to NBody] [only used when PotMod=1] @@ -90,61 +90,57 @@ False Echo - Echo the input file data (flag) 0.00E+00 8.92E+06 0.00E+00 1.68E+10 0.00E+00 0.00E+00 -8.92E+06 0.00E+00 0.00E+00 0.00E+00 1.68E+10 0.00E+00 0.00E+00 0.00E+00 0.00E+00 0.00E+00 0.00E+00 4.80E+10 ----------------------- AXIAL COEFFICIENTS -------------------------------------- - 1 NAxCoef - Number of axial coefficients (-) -AxCoefID AxCd AxCa AxCp - (-) (-) (-) (-) - 1 0.00 0.00 0.00 ----------------------- MEMBER JOINTS ------------------------------------------- - 2 NJoints - Number of joints (-) [must be exactly 0 or at least 2] -JointID Jointxi Jointyi Jointzi JointAxID JointOvrlp [JointOvrlp= 0: do nothing at joint, 1: eliminate overlaps by calculating super member] - (-) (m) (m) (m) (-) (switch) - 1 0.00000 0.00000 -13.18 1 0 - 2 0.00000 0.00000 -14.18 1 0 ----------------------- MEMBER CROSS-SECTION PROPERTIES ------------------------- - 1 NPropSets - Number of member property sets (-) -PropSetID PropD PropThck - (-) (m) (m) - 1 .00001 0.000001 +---------------------- AXIAL COEFFICIENTS -------------------------------------- +1 NAxCoef - Number of axial coefficients (-) + AxCoefID AxCd AxCa AxCp + (-) (-) (-) (-) + 1 0.0 0.0 1.0 +---------------------- MEMBER JOINTS ------------------------------------------- +0 NJoints - Number of joints (-) [must be exactly 0 or at least 2] + JointID Jointxi Jointyi Jointzi JointAxID JointOvrlp [JointOvrlp= 0: do nothing at joint, 1: eliminate overlaps by calculating super member] + (-) (m) (m) (m) (-) (switch) +---------------------- MEMBER CROSS-SECTION PROPERTIES ------------------------- +0 NPropSets - Number of member property sets (-) + PropSetID PropD PropThck + (-) (m) (m) ---------------------- SIMPLE HYDRODYNAMIC COEFFICIENTS (model 1) -------------- - SimplCd SimplCdMG SimplCa SimplCaMG SimplCp SimplCpMG SimplAxCd SimplAxCdMG SimplAxCa SimplAxCaMG SimplAxCp SimplAxCpMG - (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) - 1.00 1.00 1.00 1.00 1.00 1.00 1.00 0.00 0.00 1.00 1.00 1.00 ----------------------- DEPTH-BASED HYDRODYNAMIC COEFFICIENTS (model 2) --------- - 0 NCoefDpth - Number of depth-dependent coefficients (-) -Dpth DpthCd DpthCdMG DpthCa DpthCaMG DpthCp DpthCpMG DpthAxCa DpthAxCaMG DpthAxCp DpthAxCpMG -(m) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) ----------------------- MEMBER-BASED HYDRODYNAMIC COEFFICIENTS (model 3) -------- - 0 NCoefMembers - Number of member-based coefficients (-) -MemberID MemberCd1 MemberCd2 MemberCdMG1 MemberCdMG2 MemberCa1 MemberCa2 MemberCaMG1 MemberCaMG2 MemberCp1 MemberCp2 MemberCpMG1 MemberCpMG2 MemberAxCa1 MemberAxCa2 MemberAxCaMG1 MemberAxCaMG2 MemberAxCp1 MemberAxCp2 MemberAxCpMG1 MemberAxCpMG2 - (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) --------------------- MEMBERS ------------------------------------------------- - 1 NMembers - Number of members (-) -MemberID MJointID1 MJointID2 MPropSetID1 MPropSetID2 MDivSize MCoefMod PropPot [MCoefMod=1: use simple coeff table, 2: use depth-based coeff table, 3: use member-based coeff table] [ PropPot/=0 if member is modeled with potential-flow theory] - (-) (-) (-) (-) (-) (m) (switch) (flag) - 1 1 2 1 1 1 1 TRUE ----------------------- FILLED MEMBERS ------------------------------------------ - 0 NFillGroups - Number of filled member groups (-) [If FillDens = DEFAULT, then FillDens = WtrDens; FillFSLoc is related to MSL2SWL] -FillNumM FillMList FillFSLoc FillDens -(-) (-) (m) (kg/m^3) ----------------------- MARINE GROWTH ------------------------------------------- - 0 NMGDepths - Number of marine-growth depths specified (-) -MGDpth MGThck MGDens -(m) (m) (kg/m^3) ----------------------- MEMBER OUTPUT LIST -------------------------------------- - 0 NMOutputs - Number of member outputs (-) [must be < 10] -MemberID NOutLoc NodeLocs [NOutLoc < 10; node locations are normalized distance from the start of the member, and must be >=0 and <= 1] [unused if NMOutputs=0] - (-) (-) (-) ----------------------- JOINT OUTPUT LIST --------------------------------------- - 0 NJOutputs - Number of joint outputs [Must be < 10] - 1, 2 JOutLst - List of JointIDs which are to be output (-)[unused if NJOutputs=0] ----------------------- OUTPUT -------------------------------------------------- -TRUE HDSum - Output a summary file [flag] -False OutAll - Output all user-specified member and joint loads (only at each member end, not interior locations) [flag] - 2 OutSwtch - Output requested channels to: [1=Hydrodyn.out, 2=GlueCode.out, 3=both files] -"ES11.4e2" OutFmt - Output format for numerical results (quoted string) [not checked for validity!] -"A11" OutSFmt - Output format for header strings (quoted string) [not checked for validity!] ----------------------- OUTPUT CHANNELS ----------------------------------------- + SimplCd SimplCdMG SimplCa SimplCaMG SimplCp SimplCpMG SimplAxCd SimplAxCdMG SimplAxCa SimplAxCaMG SimplAxCp SimplAxCpMG + (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) + 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 +---------------------- DEPTH-BASED HYDRODYNAMIC COEFFICIENTS (model 2) --------- +0 NCoefDpth - Number of depth-dependent coefficients (-) + Dpth DpthCd DpthCdMG DpthCa DpthCaMG DpthCp DpthCpMG DpthAxCd DpthAxCdMG DpthAxCa DpthAxCaMG DpthAxCp DpthAxCpMG + (m) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) +---------------------- MEMBER-BASED HYDRODYNAMIC COEFFICIENTS (model 3) -------- +0 NCoefMembers - Number of member-based coefficients (-) +MemberID_HydC MemberCd1 MemberCd2 MemberCdMG1 MemberCdMG2 MemberCa1 MemberCa2 MemberCaMG1 MemberCaMG2 MemberCp1 MemberCp2 MemberCpMG1 MemberCpMG2 MemberAxCd1 MemberAxCd2 MemberAxCdMG1 MemberAxCdMG2 MemberAxCa1 MemberAxCa2 MemberAxCaMG1 MemberAxCaMG2 MemberAxCp1 MemberAxCp2 MemberAxCpMG1 MemberAxCpMG2 + (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) (-) +-------------------- MEMBERS ------------------------------------------------- +0 NMembers - Number of members (-) + MemberID MJointID1 MJointID2 MPropSetID1 MPropSetID2 MDivSize MCoefMod PropPot [MCoefMod=1: use simple coeff table, 2: use depth-based coeff table, 3: use member-based coeff table] [ PropPot/=0 if member is modeled with potential-flow theory] + (-) (-) (-) (-) (-) (m) (switch) (flag) +---------------------- FILLED MEMBERS ------------------------------------------ + 0 NFillGroups - Number of filled member groups (-) [If FillDens = DEFAULT, then FillDens = WtrDens; FillFSLoc is related to MSL2SWL] +FillNumM FillMList FillFSLoc FillDens +(-) (-) (m) (kg/m^3) +---------------------- MARINE GROWTH ------------------------------------------- + 0 NMGDepths - Number of marine-growth depths specified (-) +MGDpth MGThck MGDens +(m) (m) (kg/m^3) +---------------------- MEMBER OUTPUT LIST -------------------------------------- + 0 NMOutputs - Number of member outputs (-) [must be < 10] +MemberID NOutLoc NodeLocs [NOutLoc < 10; node locations are normalized distance from the start of the member, and must be >=0 and <= 1] [unused if NMOutputs=0] + (-) (-) (-) +---------------------- JOINT OUTPUT LIST --------------------------------------- + 0 NJOutputs - Number of joint outputs [Must be < 10] + 0 JOutLst - List of JointIDs which are to be output (-)[unused if NJOutputs=0] +---------------------- OUTPUT -------------------------------------------------- +TRUE HDSum - Output a summary file [flag] +False OutAll - Output all user-specified member and joint loads (only at each member end, not interior locations) [flag] + 2 OutSwtch - Output requested channels to: [1=Hydrodyn.out, 2=GlueCode.out, 3=both files] +"ES11.4e2" OutFmt - Output format for numerical results (quoted string) [not checked for validity!] +"A11" OutSFmt - Output format for header strings (quoted string) [not checked for validity!] +---------------------- OUTPUT CHANNELS ----------------------------------------- "Wave1Elev" - Wave elevation at the platform reference point ( 0, 0) "WavesF1xi" "WavesF1zi" diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_MoorDyn.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_MoorDyn.dat index ecb74bd9..5fae8046 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_MoorDyn.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_MoorDyn.dat @@ -1,10 +1,10 @@ --------------------- MoorDyn Input File ------------------------------------ IEA 15 MW offshore reference model on UMaine VolturnUS-S semi-submersible floating platform mooring model- C. Allen UMaine FALSE Echo - echo the input file data (flag) ------------------------ LINE TYPES ------------------------------------------ -Name Diam MassDen EA BA/-zeta EI Cd Ca CdAx CaAx -(-) (m) (kg/m) (N) (N-s/-) (-) (-) (-) (-) (-) -main 0.333 685.00 3.27E+09 -1 0 1.11 0.82 0.2 0.27 +----------------------- LINE TYPES ------------------------------------------ +Name Diam MassDen EA BA/-zeta EI Cd Ca CdAx CaAx +(-) (m) (kg/m) (N) (N-s/-) (-) (-) (-) (-) (-) +main 0.333 685.00 3.27E+09 -1.0 0 2.0 0.82 0.4 0.27 ---------------------- POINTS -------------------------------- ID Type X Y Z M V CdA CA (-) (-) (m) (m) (m) (kg) (m^3) (m^2) (-) diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ServoDyn.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ServoDyn.dat index 7ea5ee55..c2f987bd 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ServoDyn.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ServoDyn.dat @@ -17,18 +17,18 @@ False Echo - Echo input data to .ech (flag) 0.0 BlPitchF(3) - Blade 3 final pitch for pitch maneuvers (degrees) [unused for 2 blades] ---------------------- GENERATOR AND TORQUE CONTROL ---------------------------- 5 VSContrl - Variable-speed control mode {0: none, 1: simple VS, 3: user-defined from routine UserVSCont, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch) -2 GenModel - Generator model {1: simple, 2: Thevenin, 3: user-defined from routine UserGen} (switch) [used only when VSContrl=0] -96.55 GenEff - Generator efficiency [ignored by the Thevenin and user-defined generator models] (%) +1 GenModel - Generator model {1: simple, 2: Thevenin, 3: user-defined from routine UserGen} (switch) [used only when VSContrl=0] +95.756 GenEff - Generator efficiency [ignored by the Thevenin and user-defined generator models] (%) True GenTiStr - Method to start the generator {T: timed using TimGenOn, F: generator speed using SpdGenOn} (flag) True GenTiStp - Method to stop the generator {T: timed using TimGenOf, F: when generator power = 0} (flag) 9999.9 SpdGenOn - Generator speed to turn on the generator for a startup (HSS speed) (rpm) [used only when GenTiStr=False] 0.0 TimGenOn - Time to turn on the generator for a startup (s) [used only when GenTiStr=True] 9999.9 TimGenOf - Time to turn off the generator (s) [used only when GenTiStp=True] ---------------------- SIMPLE VARIABLE-SPEED TORQUE CONTROL -------------------- -9999.9 VS_RtGnSp - Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1] -9999.9 VS_RtTq - Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1] -9999.9 VS_Rgn2K - Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1] -9999.9 VS_SlPc - Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1] +7.559987120819503 VS_RtGnSp - Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1] +19624046.66639 VS_RtTq - Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1] +343357.4355671095 VS_Rgn2K - Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1] +2. VS_SlPc - Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1] ---------------------- SIMPLE INDUCTION GENERATOR ------------------------------ 9999.9 SIG_SlPc - Rated generator slip percentage (%) [used only when VSContrl=0 and GenModel=1] 9999.9 SIG_SySp - Synchronous (zero-torque) generator speed (rpm) [used only when VSContrl=0 and GenModel=1] @@ -36,7 +36,7 @@ True GenTiStp - Method to stop the generator {T: timed usin 9999.9 SIG_PORt - Pull-out ratio (Tpullout/Trated) (-) [used only when VSContrl=0 and GenModel=1] ---------------------- THEVENIN-EQUIVALENT INDUCTION GENERATOR ----------------- 9999.9 TEC_Freq - Line frequency [50 or 60] (Hz) [used only when VSContrl=0 and GenModel=2] -9998 TEC_NPol - Number of poles [even integer > 0] (-) [used only when VSContrl=0 and GenModel=2] +100 TEC_NPol - Number of poles [even integer > 0] (-) [used only when VSContrl=0 and GenModel=2] 9999.9 TEC_SRes - Stator resistance (ohms) [used only when VSContrl=0 and GenModel=2] 9999.9 TEC_RRes - Rotor resistance (ohms) [used only when VSContrl=0 and GenModel=2] 9999.9 TEC_VLL - Line-to-line RMS voltage (volts) [used only when VSContrl=0 and GenModel=2] @@ -52,10 +52,10 @@ True GenTiStp - Method to stop the generator {T: timed usin 5 YCMode - Yaw control mode {0: none, 3: user-defined from routine UserYawCont, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch) 0 TYCOn - Time to enable active yaw control (s) [unused when YCMode=0] 0.0 YawNeut - Neutral yaw position--yaw spring force is zero at this yaw (degrees) -4.6273E+10 YawSpr - Nacelle-yaw spring constant (N-m/rad) -3.9088E+07 YawDamp - Nacelle-yaw damping constant (N-m/(rad/s)) +8458453511.0 YawSpr - Nacelle-yaw spring constant (N-m/rad) +28561762.0 YawDamp - Nacelle-yaw damping constant (N-m/(rad/s)) 9999.9 TYawManS - Time to start override yaw maneuver and end standard yaw control (s) -2.0 YawManRat - Yaw maneuver rate (in absolute value) (deg/s) +0.25 YawManRat - Yaw maneuver rate (in absolute value) (deg/s) 0.0 NacYawF - Final yaw angle for override yaw maneuvers (degrees) ---------------------- AERODYNAMIC FLOW CONTROL -------------------------------- 0 AfCmode - Airfoil control mode {0: none, 1: cosine wave cycle, 4: user-defined from Simulink/Labview, 5: user-defined from Bladed-style DLL} (switch) diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_AeroDyn15.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_AeroDyn15.dat index c2602a6f..953a29a7 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_AeroDyn15.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_AeroDyn15.dat @@ -1,42 +1,44 @@ ------- AERODYN v15.03.* INPUT FILE ------------------------------------------------ IEA 15 MW Offshore Reference Turbine ====== General Options ============================================================================ -False Echo - Echo the input to ".AD.ech"? (flag) -"default" DTAero - Time interval for aerodynamic calculations {or "default"} (s) -1 WakeMod - Type of wake/induction model (switch) {0=none, 1=BEMT, 2=DBEMT, 3=OLAF} [WakeMod cannot be 2 or 3 when linearizing] -2 AFAeroMod - Type of blade airfoil aerodynamics model (switch) {1=steady model, 2=Beddoes-Leishman unsteady model} [AFAeroMod must be 1 when linearizing] -1 TwrPotent - Type tower influence on wind based on potential flow around the tower (switch) {0=none, 1=baseline potential flow, 2=potential flow with Bak correction} -1 TwrShadow - Calculate tower influence on wind based on downstream tower shadow (switch) {0=none, 1=Powles model, 2=Eames model} -True TwrAero - Calculate tower aerodynamic loads? (flag) -False FrozenWake - Assume frozen wake during linearization? (flag) [used only when WakeMod=1 and when linearizing] -False CavitCheck - Perform cavitation check? (flag) [AFAeroMod must be 1 when CavitCheck=true] -False Buoyancy - Include buoyancy effects? (flag) -False CompAA - Flag to compute AeroAcoustics calculation [used only when WakeMod = 1 or 2] -"AeroAcousticsInput.dat" AA_InputFile - AeroAcoustics input file [used only when CompAA=true] +False Echo - Echo the input to ".AD.ech"? (flag) +default DTAero - Time interval for aerodynamic calculations {or "default"} (s) +1 WakeMod - Type of wake/induction model (switch) {0=none, 1=BEMT, 2=DBEMT, 3=OLAF} [WakeMod cannot be 2 or 3 when linearizing] +2 AFAeroMod - Type of blade airfoil aerodynamics model (switch) {1=steady model, 2=Beddoes-Leishman unsteady model} [AFAeroMod must be 1 when linearizing] +1 TwrPotent - Type tower influence on wind based on potential flow around the tower (switch) {0=none, 1=baseline potential flow, 2=potential flow with Bak correction} +1 TwrShadow - Calculate tower influence on wind based on downstream tower shadow (switch) {0=none, 1=Powles model, 2=Eames model} +True TwrAero - Calculate tower aerodynamic loads? (flag) +False FrozenWake - Assume frozen wake during linearization? (flag) [used only when WakeMod=1 and when linearizing] +False CavitCheck - Perform cavitation check? (flag) [AFAeroMod must be 1 when CavitCheck=true] +False Buoyancy - Include buoyancy effects? (flag) +False CompAA - Flag to compute AeroAcoustics calculation [only used when WakeMod=1 or 2] +AeroAcousticsInput.dat AA_InputFile - AeroAcoustics input file [used only when CompAA=true] ====== Environmental Conditions =================================================================== -"default" AirDens - Air density (kg/m^3) -"default" KinVisc - Kinematic air viscosity (m^2/s) -"default" SpdSound - Speed of sound (m/s) -"default" Patm - Atmospheric pressure (Pa) [used only when CavitCheck=True] -"default" Pvap - Vapour pressure of fluid (Pa) [used only when CavitCheck=True] +"default" AirDens - Air density (kg/m^3) +"default" KinVisc - Kinematic air viscosity (m^2/s) +"default" SpdSound - Speed of sound (m/s) +"default" Patm - Atmospheric pressure (Pa) [used only when CavitCheck=True] +"default" Pvap - Vapour pressure of fluid (Pa) [used only when CavitCheck=True] ====== Blade-Element/Momentum Theory Options ====================================================== [used only when WakeMod=1] 2 SkewMod - Type of skewed-wake correction model (switch) {1=uncoupled, 2=Pitt/Peters, 3=coupled} [unused when WakeMod=0 or 3] -"default" SkewModFactor - Constant used in Pitt/Peters skewed wake model {or "default" is 15/32*pi} (-) [used only when SkewMod=2; unused when WakeMod=0 or 3] +default SkewModFactor - Constant used in Pitt/Peters skewed wake model {or "default" is 15/32*pi} (-) [used only when SkewMod=2; unused when WakeMod=0 or 3] True TipLoss - Use the Prandtl tip-loss model? (flag) [unused when WakeMod=0 or 3] True HubLoss - Use the Prandtl hub-loss model? (flag) [unused when WakeMod=0 or 3] True TanInd - Include tangential induction in BEMT calculations? (flag) [unused when WakeMod=0 or 3] True AIDrag - Include the drag term in the axial-induction calculation? (flag) [unused when WakeMod=0 or 3] True TIDrag - Include the drag term in the tangential-induction calculation? (flag) [unused when WakeMod=0,3 or TanInd=FALSE] -"Default" IndToler - Convergence tolerance for BEMT nonlinear solve residual equation {or "default"} (-) [unused when WakeMod=0 or 3] +default IndToler - Convergence tolerance for BEMT nonlinear solve residual equation {or "default"} (-) [unused when WakeMod=0 or 3] 500 MaxIter - Maximum number of iteration steps (-) [unused when WakeMod=0] ====== Dynamic Blade-Element/Momentum Theory Options ====================================================== [used only when WakeMod=1] 2 DBEMT_Mod - Type of dynamic BEMT (DBEMT) model {1=constant tau1, 2=time-dependent tau1} (-) [used only when WakeMod=2] -2 tau1_const - Time constant for DBEMT (s) [used only when WakeMod=2 and DBEMT_Mod=1] +29.03 tau1_const - Time constant for DBEMT (s) [used only when WakeMod=2 and DBEMT_Mod=1] ====== OLAF -- cOnvecting LAgrangian Filaments (Free Vortex Wake) Theory Options ================== [used only when WakeMod=3] -"unused" OLAFInputFileName - Input file for OLAF [used only when WakeMod=3] +IEA-15-240-RWT_OLAF.dat OLAFInputFileName - Input file for OLAF [used only when WakeMod=3] ====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2] 3 UAMod - Unsteady Aero Model Switch (switch) {1=Baseline model (Original), 2=Gonzalez's variant (changes in Cn,Cc,Cm), 3=Minnema/Pierce variant (changes in Cc and Cm)} [used only when AFAeroMod=2] True FLookup - Flag to indicate whether a lookup for f' will be calculated (TRUE) or whether best-fit exponential equations will be used (FALSE); if FALSE S1-S4 must be provided in airfoil input files (flag) [used only when AFAeroMod=2] +0.1 UAStartRad - Starting radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2] +1.0 UAEndRad - Ending radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2] ====== Airfoil Information ========================================================================= 1 AFTabMod - Interpolation method for multiple airfoil tables {1=1D interpolation on AoA (first table only); 2=2D interpolation on AoA and Re; 3=2D interpolation on AoA and UserProp} (-) 1 InCol_Alfa - The column in the airfoil tables that contains the angle of attack (-) @@ -109,21 +111,21 @@ True UseBlCm - Include aerodynamic pitching moment in calc ====== Tail fin Aerodynamics ======================================================================== False TFinAero - Calculate tail fin aerodynamics model (flag) "unused" TFinFile - Input file for tail fin aerodynamics [used only when TFinAero=True] -====== Tower Influence and Aerodynamics ============================================================ [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] - 11 NumTwrNds - Number of tower nodes used in the analysis (-) [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] -TwrElev TwrDiam TwrCd TwrTI TwrCb !TwrTI used only with TwrShadow=2, TwrCb used only with Buoyancy=True -(m) (m) (-) (-) (-) - 15. 10. 0.5 0.1 0.0 - 28. 10. 0.5 0.1 0.0 - 41. 9.926 0.5 0.1 0.0 - 54. 9.443 0.5 0.1 0.0 - 67. 8.833 0.5 0.1 0.0 - 80. 8.151 0.5 0.1 0.0 - 93. 7.39 0.5 0.1 0.0 - 106. 6.909 0.5 0.1 0.0 - 119. 6.748 0.5 0.1 0.0 - 132. 6.572 0.5 0.1 0.0 - 144.386 6.5 0.5 0.1 0.0 +====== Tower Influence and Aerodynamics ============================================================= [used only when TwrPotent/=0, TwrShadow/=0, or TwrAero=True] +11 NumTwrNds - Number of tower nodes used in the analysis (-) [used only when TwrPotent/=0, TwrShadow/=0, or TwrAero=True] +TwrElev TwrDiam TwrCd TwrTI TwrCb !TwrTI used only with TwrShadow=2, TwrCb used only with Buoyancy=True +(m) (m) (-) (-) (-) + 15. 10. 0.5 0.1 0.0 + 28. 10. 0.5 0.1 0.0 + 41. 10. 0.5 0.1 0.0 + 54. 10. 0.5 0.1 0.0 + 67. 10. 0.5 0.1 0.0 + 80. 10. 0.5 0.1 0.0 + 93. 10. 0.5 0.1 0.0 + 106. 10. 0.5 0.1 0.0 + 119. 10. 0.5 0.1 0.0 + 132. 10. 0.5 0.1 0.0 + 144.386 6.5 0.5 0.1 0.0 ====== Outputs ==================================================================================== True SumPrint - Generate a summary file listing input options and interpolated properties to ".AD.sum"? (flag) 9 NBlOuts - Number of blade node outputs [0 - 9] (-) diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_AeroDyn15_blade.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_AeroDyn15_blade.dat index ad2eb94b..1857ef2d 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_AeroDyn15_blade.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_AeroDyn15_blade.dat @@ -2,55 +2,55 @@ IEA 15 MW Offshore Reference Turbine ====== Blade Properties ================================================================= 50 NumBlNds - Number of blade nodes used in the analysis (-) - BlSpn BlCrvAC BlSwpAC BlCrvAng BlTwist BlChord BlAFID - (m) (m) (m) (deg) (deg) (m) (-) - 0.000000000000000e+00 0.000000000000000e+00 0.000000000000000e+00 4.389598567857100e-01 1.559455301971172e+01 5.200000000000000e+00 1 - 2.340000000000000e+00 1.792725442100923e-02 0.000000000000000e+00 5.032657169918083e-01 1.559105026258913e+01 5.208280051053228e+00 2 - 4.680000000000000e+00 4.110692427421048e-02 0.000000000000000e+00 6.308553568297277e-01 1.542808288705693e+01 5.235714686841762e+00 3 - 7.020000000000000e+00 6.945536768748266e-02 0.000000000000000e+00 7.335329065217842e-01 1.498668187913840e+01 5.288938619667076e+00 4 - 9.359999999999999e+00 1.010212888733921e-01 0.000000000000000e+00 7.884297977029056e-01 1.432158034416253e+01 5.360587950371896e+00 5 - 1.170000000000000e+01 1.338533920445052e-01 0.000000000000000e+00 7.909585172161996e-01 1.348751138745829e+01 5.443298779798948e+00 6 - 1.462500000000000e+01 1.737014122489205e-01 0.000000000000000e+00 7.327637065640680e-01 1.229069721992214e+01 5.551024109038494e+00 7 - 1.755000000000000e+01 2.086678175525200e-01 0.000000000000000e+00 6.223844458530188e-01 1.102229252935764e+01 5.650144322056736e+00 8 - 1.977698541208247e+01 2.296645661376480e-01 0.000000000000000e+00 4.537499627775453e-01 1.007455100521850e+01 5.710964180985916e+00 9 - 2.200397082416493e+01 2.439403627159931e-01 0.000000000000000e+00 2.591924634298315e-01 9.194457415112664e+00 5.752111033293940e+00 10 - 2.423095623624740e+01 2.498132008590583e-01 0.000000000000000e+00 8.141948146465851e-02 8.429191400183106e+00 5.767237237684651e+00 11 - 2.645794164832986e+01 2.502696224973349e-01 0.000000000000000e+00 -5.201336270782935e-03 7.777140178454876e+00 5.754540379641527e+00 12 - 2.868492706041233e+01 2.494088674131781e-01 0.000000000000000e+00 -3.406772178568601e-02 7.182453068336759e+00 5.702616552569126e+00 13 - 3.113238085174112e+01 2.474902295602668e-01 0.000000000000000e+00 -5.578985889668429e-02 6.526991264456793e+00 5.600650141179936e+00 14 - 3.357983464306991e+01 2.446426147761379e-01 0.000000000000000e+00 -7.615697459071377e-02 5.894967665228040e+00 5.463153391746188e+00 15 - 3.602728843439870e+01 2.409839694867318e-01 0.000000000000000e+00 -9.543755013755111e-02 5.294241247126913e+00 5.309456651571882e+00 16 - 3.847474222572749e+01 2.364891735317261e-01 0.000000000000000e+00 -1.077434001298583e-01 4.734510589122642e+00 5.148771194775275e+00 17 - 4.105659048741643e+01 2.315264878237667e-01 0.000000000000000e+00 -1.480006043120704e-01 4.200509221861605e+00 4.991052530953460e+00 18 - 4.363843874910536e+01 2.231508550279065e-01 0.000000000000000e+00 -2.942923602503220e-01 3.725899877374307e+00 4.849825861125237e+00 19 - 4.622028701079431e+01 2.050039451777621e-01 0.000000000000000e+00 -5.513815357366169e-01 3.306980159403296e+00 4.727623031975457e+00 20 - 4.880213527248324e+01 1.734591849365768e-01 0.000000000000000e+00 -8.953005634818914e-01 2.919972991579771e+00 4.604744127582399e+00 21 - 5.138398353417219e+01 1.243196031004582e-01 0.000000000000000e+00 -1.185431256004288e+00 2.561013760569935e+00 4.482053325831189e+00 22 - 5.368869775367514e+01 7.236499116496864e-02 0.000000000000000e+00 -1.374054599116387e+00 2.261976958738843e+00 4.373759436309791e+00 23 - 5.599341197317808e+01 1.378791448434181e-02 0.000000000000000e+00 -1.516545898214346e+00 1.980308613217369e+00 4.267298674782820e+00 24 - 5.829812619268102e+01 -4.962643021848042e-02 0.000000000000000e+00 -1.593149607978640e+00 1.713584420221966e+00 4.162982209701337e+00 25 - 6.060284041218397e+01 -1.143639830605745e-01 0.000000000000000e+00 -1.668831089428184e+00 1.457959216148460e+00 4.061706722205011e+00 26 - 6.290755463168692e+01 -1.838644133413873e-01 0.000000000000000e+00 -1.909518357572825e+00 1.215627353698105e+00 3.963536198880925e+00 27 - 6.526010287719268e+01 -2.695496189370229e-01 0.000000000000000e+00 -2.247888332111739e+00 9.878931973599971e-01 3.866942578335688e+00 28 - 6.761265112269844e+01 -3.684123593201381e-01 0.000000000000000e+00 -2.582649071388314e+00 7.751486517583764e-01 3.773008482150572e+00 29 - 6.996519936820421e+01 -4.815634639349944e-01 0.000000000000000e+00 -2.865294558288838e+00 5.753772042113692e-01 3.681310369877000e+00 30 - 7.231774761370995e+01 -6.036106395386901e-01 0.000000000000000e+00 -3.067504785280989e+00 3.801903461857860e-01 3.590736963146067e+00 31 - 7.467029585921573e+01 -7.333448728858328e-01 0.000000000000000e+00 -3.208584670401211e+00 1.859865520515259e-01 3.500781512082179e+00 32 - 7.690225798158134e+01 -8.602107347043737e-01 0.000000000000000e+00 -3.290027380374246e+00 -1.895066028803559e-03 3.415119535682277e+00 33 - 7.913422010394696e+01 -9.895306443763798e-01 0.000000000000000e+00 -3.333478315696412e+00 -2.032949456984741e-01 3.328844727050613e+00 34 - 8.136618222631259e+01 -1.119776122673767e+00 0.000000000000000e+00 -3.432368423138003e+00 -4.252875829492346e-01 3.241551330883462e+00 35 - 8.359814434867820e+01 -1.256787151546890e+00 0.000000000000000e+00 -3.619769014840467e+00 -6.835362560574688e-01 3.155076129554687e+00 36 - 8.583010647104382e+01 -1.401605396595971e+00 0.000000000000000e+00 -3.806658744089384e+00 -9.818668004993735e-01 3.069529014714899e+00 37 - 8.806206859340944e+01 -1.553146463694890e+00 0.000000000000000e+00 -3.974642514158079e+00 -1.283187977449598e+00 2.983961316513787e+00 38 - 9.029403071577507e+01 -1.711022186839844e+00 0.000000000000000e+00 -4.157561213452237e+00 -1.575204470207721e+00 2.898006382996998e+00 39 - 9.360000000000001e+01 -1.954643553943418e+00 0.000000000000000e+00 -4.282127409053577e+00 -1.936867726960525e+00 2.768221228578391e+00 40 - 9.579375000000002e+01 -2.121673387702402e+00 0.000000000000000e+00 -4.415936480162901e+00 -2.107559875105575e+00 2.679571699358601e+00 41 - 9.798750000000000e+01 -2.292465037138542e+00 0.000000000000000e+00 -4.515395367110078e+00 -2.166589245326676e+00 2.588234998923033e+00 42 - 1.001812500000000e+02 -2.467087944121202e+00 0.000000000000000e+00 -4.647677691199882e+00 -2.176064619564126e+00 2.493925003782623e+00 43 - 1.023750000000000e+02 -2.647976917310403e+00 0.000000000000000e+00 -4.809336627570893e+00 -2.161185304881369e+00 2.397357498996977e+00 44 - 1.045687500000000e+02 -2.834936933971896e+00 0.000000000000000e+00 -4.968453379562535e+00 -2.118517957471362e+00 2.298574617144009e+00 45 - 1.067625000000000e+02 -3.027966149204049e+00 0.000000000000000e+00 -5.119883153423658e+00 -2.048882314259705e+00 2.197674647152629e+00 46 - 1.089562500000000e+02 -3.226477188906264e+00 0.000000000000000e+00 -5.267217867902559e+00 -1.951426912022273e+00 2.094746664459376e+00 47 - 1.111500000000000e+02 -3.430742432797884e+00 0.000000000000000e+00 -5.432171356025582e+00 -1.815172386244977e+00 1.989485429115948e+00 48 - 1.140750000000000e+02 -3.711055444100119e+00 0.000000000000000e+00 -5.584230840524383e+00 -1.567929958032109e+00 1.848333283013637e+00 49 - 1.170000000000000e+02 -3.999999999999996e+00 0.000000000000000e+00 -5.669178789134813e+00 -1.242387706272969e+00 5.000000000000001e-01 50 + BlSpn BlCrvAC BlSwpAC BlCrvAng BlTwist BlChord BlAFID BlCb BlCenBn BlCenBt + (m) (m) (m) (deg) (deg) (m) (-) (-) (m) (m) + 0.000000000000000e+00 -6.354122360450852e-03 -2.276626484469566e-02 9.291281525327398e-01 1.559455301971172e+01 5.200000000000000e+00 1 0.0 0.0 0.0 + 2.387753704536792e+00 3.236481948738088e-02 5.005748522338992e-02 8.707285997270117e-01 1.558773861176889e+01 5.208839941579524e+00 2 0.0 0.0 0.0 + 4.775507409073585e+00 6.621685687511680e-02 8.694386659281718e-02 6.376768648563605e-01 1.541083467878359e+01 5.237887092263203e+00 3 0.0 0.0 0.0 + 7.163261113610377e+00 8.551302257769909e-02 5.307191353698237e-02 3.623009655957606e-01 1.494855563474368e+01 5.293325313383697e+00 4 0.0 0.0 0.0 + 9.551014818147170e+00 9.641383525966472e-02 -2.834268227993915e-02 2.309264254802593e-01 1.425845480678574e+01 5.367339854814920e+00 5 0.0 0.0 0.0 + 1.193876852268396e+01 1.047603018628692e-01 -1.352768396731961e-01 2.332510218907787e-01 1.339714163725627e+01 5.452092684226667e+00 6 0.0 0.0 0.0 + 1.432652222722075e+01 1.158548641787537e-01 -2.434441389056812e-01 3.537684475592492e-01 1.242201947682708e+01 5.540031728503847e+00 7 0.0 0.0 0.0 + 1.671427593175755e+01 1.342461230233627e-01 -3.188598483871042e-01 5.253284774395157e-01 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-1.896743213972770e+00 2.052625082558482e+00 47 0.0 0.0 0.0 + 1.122244241132292e+02 -3.527723381568596e+00 -1.989581851179342e-01 -5.490470005410412e+00 -1.724325762660474e+00 1.937753326819164e+00 48 0.0 0.0 0.0 + 1.146121778177661e+02 -3.758854692855718e+00 -2.002555383444301e-01 -5.660129840633894e+00 -1.508125114401624e+00 1.819662967336163e+00 49 0.0 0.0 0.0 + 1.169999315223028e+02 -3.998718787548573e+00 -5.907701779748526e-02 -5.765427375220712e+00 -1.242387706272970e+00 4.999999999999998e-01 50 0.0 0.0 0.0 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_BeamDyn.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_BeamDyn.dat index 9efc0c85..793a44fe 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_BeamDyn.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_BeamDyn.dat @@ -20,75 +20,76 @@ True RotStates - Orient states in the rotating frame during linea 1 member_total - Total number of members (-) 50 kp_total - Total number of key points (-) [must be at least 3] 1 50 - Member number; Number of key points in this member - kp_xr kp_yr kp_zr initial_twist - (m) (m) (m) (deg) - 0.00000e+00 0.00000e+00 0.00000e+00 1.55946e+01 - 1.84435e-02 0.00000e+00 2.38776e+00 1.55848e+01 - 4.42547e-02 0.00000e+00 4.77551e+00 1.52722e+01 - 7.04469e-02 0.00000e+00 7.16327e+00 1.49320e+01 - 1.02607e-01 0.00000e+00 9.55102e+00 1.41587e+01 - 1.34578e-01 0.00000e+00 1.19388e+01 1.33615e+01 - 1.64841e-01 0.00000e+00 1.43265e+01 1.23499e+01 - 1.95104e-01 0.00000e+00 1.67143e+01 1.13382e+01 - 2.19251e-01 0.00000e+00 1.91020e+01 1.03407e+01 - 2.38876e-01 0.00000e+00 2.14898e+01 9.36880e+00 - 2.46864e-01 0.00000e+00 2.38776e+01 8.56794e+00 - 2.50137e-01 0.00000e+00 2.62653e+01 7.84623e+00 - 2.49410e-01 0.00000e+00 2.86531e+01 7.19164e+00 - 2.47109e-01 0.00000e+00 3.10408e+01 6.56300e+00 - 2.44787e-01 0.00000e+00 3.34286e+01 5.93471e+00 - 2.40916e-01 0.00000e+00 3.58163e+01 5.36469e+00 - 2.36941e-01 0.00000e+00 3.82041e+01 4.79861e+00 - 2.31729e-01 0.00000e+00 4.05918e+01 4.31242e+00 - 2.25412e-01 0.00000e+00 4.29796e+01 3.84376e+00 - 2.08839e-01 0.00000e+00 4.53673e+01 3.45434e+00 - 1.85567e-01 0.00000e+00 4.77551e+01 3.07869e+00 - 1.45267e-01 0.00000e+00 5.01429e+01 2.73806e+00 - 9.72760e-02 0.00000e+00 5.25306e+01 2.41518e+00 - 4.09587e-02 0.00000e+00 5.49184e+01 2.11152e+00 - -2.32178e-02 0.00000e+00 5.73061e+01 1.83141e+00 - -8.97487e-02 0.00000e+00 5.96939e+01 1.56018e+00 - -1.59634e-01 0.00000e+00 6.20816e+01 1.30414e+00 - -2.43603e-01 0.00000e+00 6.44694e+01 1.06774e+00 - -3.35292e-01 0.00000e+00 6.68571e+01 8.41981e-01 - -4.49346e-01 0.00000e+00 6.92449e+01 6.38167e-01 - -5.69003e-01 0.00000e+00 7.16327e+01 4.36820e-01 - -6.98204e-01 0.00000e+00 7.40204e+01 2.39673e-01 - -8.32976e-01 0.00000e+00 7.64082e+01 3.60946e-02 - -9.70169e-01 0.00000e+00 7.87959e+01 -1.73247e-01 - -1.11069e+00 0.00000e+00 8.11837e+01 -4.15724e-01 - -1.25730e+00 0.00000e+00 8.35714e+01 -6.89429e-01 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1.02673e+02 -2.15530e+00 + -2.87783e+00 0.00000e+00 1.05061e+02 -2.10291e+00 + -3.09009e+00 0.00000e+00 1.07449e+02 -2.01840e+00 + -3.30846e+00 0.00000e+00 1.09837e+02 -1.89674e+00 + -3.53371e+00 0.00000e+00 1.12224e+02 -1.72433e+00 + -3.76350e+00 0.00000e+00 1.14612e+02 -1.50813e+00 + -4.00000e+00 0.00000e+00 1.17000e+02 -1.24239e+00 ---------------------- MESH PARAMETER ------------------------------------------ - 5 order_elem - Order of interpolation (basis) function (-) + 10 order_elem - Order of interpolation (basis) function (-) ---------------------- MATERIAL PARAMETER -------------------------------------- -"IEA 15MW Offshore Reference Turbine, with taped chord tip design_BeamDyn_Blade.dat" BldFile - Name of file containing properties for blade (quoted string) +"IEA-15-240-RWT_BeamDyn_blade.dat" BldFile - Name of file containing properties for blade (quoted string) ---------------------- PITCH ACTUATOR PARAMETERS ------------------------------- False UsePitchAct - Whether a pitch actuator should be used (flag) 200 PitchJ - Pitch actuator inertia (kg-m^2) [used only when UsePitchAct is true] 2E+07 PitchK - Pitch actuator stiffness (kg-m^2/s^2) [used only when UsePitchAct is true] 500000 PitchC - Pitch actuator damping (kg-m^2/s) [used only when UsePitchAct is true] ---------------------- OUTPUTS ------------------------------------------------- -True SumPrint - Print summary data to ".sum" (flag) -"ES10.3E2" OutFmt - Format used for text tabular output, excluding the time channel. - 1 NNodeOuts - Number of nodes to output to file [0 - 9] (-) - 1, 2, 3, 4, 5, 6 OutNd - Nodes whose values will be output (-) +False SumPrint - Print summary data to ".sum" (flag) +"ES10.3E2" OutFmt - Format used for text tabular output, excluding the time channel. + 0 NNodeOuts - Number of nodes to output to file [0 - 9] (-) + 0 OutNd - Nodes whose values will be output (-) OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) "RootFxr, RootFyr, RootFzr" "RootMxr, RootMyr, RootMzr" "TipTDxr, TipTDyr, TipTDzr" +"TipRDxr, TipRDyr, TipRDzr" END of input file (the word "END" must appear in the first 3 columns of this last OutList line) --------------------------------------------------------------------------------------- diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_BeamDyn_blade.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_BeamDyn_blade.dat index 47f10ec1..00ce4392 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_BeamDyn_blade.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_BeamDyn_blade.dat @@ -1,325 +1,400 @@ ------- BEAMDYN V1.00.* INDIVIDUAL BLADE INPUT FILE -------------------------- IEA 15MW Offshore Reference Turbine, with taped chord tip design blade. Generated with Sonata/ANBA4 by Roland Feil et al (A Cross-Sectional Aeroelastic Analysis and Structural Optimization Tool for Slender Composite Structures) ---------------------- BLADE PARAMETERS -------------------------------------- -21 station_total - Number of blade input stations (-) +26 station_total - Number of blade input stations (-) 1 damp_type - Damping type: 0: no damping; 1: damped ---------------------- DAMPING COEFFICIENT------------------------------------ mu1 mu2 mu3 mu4 mu5 mu6 (-) (-) (-) (-) (-) (-) -1.0E-02 1.0E-02 1.0E-02 1.0E-02 1.0E-02 1.0E-02 + 0.00299005 0.00218775 0.00084171 0.00218775 0.00299005 0.00084171 ---------------------- DISTRIBUTED PROPERTIES--------------------------------- 0.000000 - 6.7405384666796303e+09 2.5383906981772380e+06 0.0000000000000000e+00 0.0000000000000000e+00 0.0000000000000000e+00 1.4854220798940736e+08 - 2.5383906987799853e+06 6.7281514263933067e+09 0.0000000000000000e+00 0.0000000000000000e+00 0.0000000000000000e+00 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1.5888593660892941e-01 9.3734276922887980e-02 -2.2768326051883147e-03 0.0000000000000000e+00 + 0.0000000000000000e+00 0.0000000000000000e+00 -3.6961089182658016e-02 -2.2768326051883147e-03 7.1808104318029677e-03 0.0000000000000000e+00 + -1.5888593660892941e-01 3.6961089182658016e-02 0.0000000000000000e+00 0.0000000000000000e+00 0.0000000000000000e+00 1.0091508735469075e-01 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_ElastoDyn_blade.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_ElastoDyn_blade.dat index 6763582d..1402b0b4 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_ElastoDyn_blade.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_ElastoDyn_blade.dat @@ -2,9 +2,9 @@ IEA 15 MW Offshore Reference Turbine ---------------------- BLADE PARAMETERS ---------------------------------------- 50 NBlInpSt - Number of blade input stations (-) -3.0 BldFlDmp1 - Blade flap mode #1 structural damping in percent of critical (%) -3.0 BldFlDmp2 - Blade flap mode #2 structural damping in percent of critical (%) -3.0 BldEdDmp1 - Blade edge mode #1 structural damping in percent of critical (%) +0.48 BldFlDmp1 - Blade flap mode #1 structural damping in percent of critical (%) +0.48 BldFlDmp2 - Blade flap mode #2 structural damping in percent of critical (%) +0.48 BldEdDmp1 - Blade edge mode #1 structural damping in percent of critical (%) ---------------------- BLADE ADJUSTMENT FACTORS -------------------------------- 1.0 FlStTunr1 - Blade flapwise modal stiffness tuner, 1st mode (-) 1.0 FlStTunr2 - Blade flapwise modal stiffness tuner, 2nd mode (-) @@ -14,69 +14,69 @@ IEA 15 MW Offshore Reference Turbine ---------------------- DISTRIBUTED BLADE PROPERTIES ---------------------------- BlFract PitchAxis StrcTwst BMassDen FlpStff EdgStff (-) (-) (deg) (kg/m) (Nm^2) (Nm^2) - 0.000000000000000e+00 5.045454545454545e-01 1.559455301971172e+01 3.179059159259066e+03 1.525336732671642e+11 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3.460555975714659e-01 -1.896743213972770e+00 3.669679320964971e+01 4.921992371612750e+07 1.631692262693548e+08 + 9.591836734693876e-01 3.527211856428439e-01 -1.724325762660474e+00 2.687365619764821e+01 2.743282717773140e+07 1.064318616320310e+08 + 9.795918367346939e-01 3.600890296396286e-01 -1.508125114401624e+00 2.157201084316552e+01 1.296677095760643e+07 6.715371720843673e+07 + 1.000000000000000e+00 3.681818181818181e-01 -1.242387706272970e+00 5.767382468564499e+00 1.862011072702549e+05 1.663313892259768e+06 ---------------------- BLADE MODE SHAPES --------------------------------------- -0.013253949170547142 BldFl1Sh(2) - Flap mode 1, coeff of x^2 -2.0969905409500766 BldFl1Sh(3) - , coeff of x^3 --2.1551003508095734 BldFl1Sh(4) - , coeff of x^4 -1.7659262841662073 BldFl1Sh(5) - , coeff of x^5 --0.7210704234772579 BldFl1Sh(6) - , coeff of x^6 -0.03008779134485143 BldFl2Sh(2) - Flap mode 2, coeff of x^2 -2.3249755647623678 BldFl2Sh(3) - , coeff of x^3 --4.012699218410927 BldFl2Sh(4) - , coeff of x^4 -4.5046974670633055 BldFl2Sh(5) - , coeff of x^5 --1.8470616047595974 BldFl2Sh(6) - , coeff of x^6 --0.017374330365441948 BldEdgSh(2) - Edge mode 1, coeff of x^2 -3.0497818094928792 BldEdgSh(3) - , coeff of x^3 --3.7004075077120575 BldEdgSh(4) - , coeff of x^4 -2.5651437910431514 BldEdgSh(5) - , coeff of x^5 --0.8971437624585316 BldEdgSh(6) - , coeff of x^6 +-0.0752915102669993 BldFl1Sh(2) - Flap mode 1, coeff of x^2 +2.826459690437861 BldFl1Sh(3) - , coeff of x^3 +-3.2702836497367604 BldFl1Sh(4) - , coeff of x^4 +2.252110669909933 BldFl1Sh(5) - , coeff of x^5 +-0.7329952003440339 BldFl1Sh(6) - , coeff of x^6 +-0.5285519130664843 BldFl2Sh(2) - Flap mode 2, coeff of x^2 +0.7090455925619575 BldFl2Sh(3) - , coeff of x^3 +-7.795036256009813 BldFl2Sh(4) - , coeff of x^4 +15.797380956455061 BldFl2Sh(5) - , coeff of x^5 +-7.182838379940722 BldFl2Sh(6) - , coeff of x^6 +-0.02913195484596477 BldEdgSh(2) - Edge mode 1, coeff of x^2 +5.270503361982258 BldEdgSh(3) - , coeff of x^3 +-11.024746168421133 BldEdgSh(4) - , coeff of x^4 +10.34151438983642 BldEdgSh(5) - , coeff of x^5 +-3.5581396285515794 BldEdgSh(6) - , coeff of x^6 diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_InflowFile.dat b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_InflowFile.dat index bc188532..e51a1962 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_InflowFile.dat +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_InflowFile.dat @@ -15,18 +15,18 @@ False VelInterpCubic - Use cubic interpolation for velocity in tim 150.0 RefHt - Reference height for horizontal wind speed (m) 0.12 PLexp - Power law exponent (-) ================== Parameters for Uniform wind file [used only for WindType = 2] ============================ -"Wind/NoShr_9-14_Inc1_50s.wnd" Filename_Uni - Filename of time series data for uniform wind field. (-) -150.0 RefHt_Uni - Reference height for horizontal wind speed (m) -125.88 RefLength - Reference length for linear horizontal and vertical sheer (-) +"none" Filename_Uni - Filename of time series data for uniform wind field. (-) +150.0 RefHt_Uni - Reference height for horizontal wind speed (m) +240.0 RefLength - Reference length for linear horizontal and vertical sheer (-) ================== Parameters for Binary TurbSim Full-Field files [used only for WindType = 3] ============== -"Wind/145m_11mps_ClassA1ETM.bts" FileName_BTS - Name of the Full field wind file to use (.bts) +"none" FileName_BTS - Name of the Full field wind file to use (.bts) ================== Parameters for Binary Bladed-style Full-Field files [used only for WindType = 4] ========= -"Wind/90m_12mps_twr" FilenameRoot - Rootname of the full-field wind file to use (.wnd, .sum) +"none" FilenameRoot - Rootname of the full-field wind file to use (.wnd, .sum) False TowerFile - Have tower file (.twr) (flag) ================== Parameters for HAWC-format binary files [Only used with WindType = 5] ===================== -"wasp/Output/basic_5u.bin" FileName_u - name of the file containing the u-component fluctuating wind (.bin) -"wasp/Output/basic_5v.bin" FileName_v - name of the file containing the v-component fluctuating wind (.bin) -"wasp/Output/basic_5w.bin" FileName_w - name of the file containing the w-component fluctuating wind (.bin) +"none" FileName_u - name of the file containing the u-component fluctuating wind (.bin) +"none" FileName_v - name of the file containing the v-component fluctuating wind (.bin) +"none" FileName_w - name of the file containing the w-component fluctuating wind (.bin) 64 nx - number of grids in the x direction (in the 3 files above) (-) 32 ny - number of grids in the y direction (in the 3 files above) (-) 32 nz - number of grids in the z direction (in the 3 files above) (-) @@ -47,7 +47,7 @@ False TowerFile - Have tower file (.twr) (flag) 2 WindProfile - Wind profile type (0=constant;1=logarithmic,2=power law) 0.2 PLExp_Hawc - Power law exponent (-) (used for PL wind profile type only) 0.03 Z0 - Surface roughness length (m) (used for LG wind profile type only) -0 XOffset - Initial offset in +x direction (shift of wind box) +0 XOffset - Initial offset in +x direction (shift of wind box) (-) ================== LIDAR Parameters =========================================================================== 0 SensorType - Switch for lidar configuration (0 = None, 1 = Single Point Beam(s), 2 = Continuous, 3 = Pulsed) 0 NumPulseGate - Number of lidar measurement gates (used when SensorType = 3) @@ -65,5 +65,7 @@ False LidRadialVel - TRUE => return radial component, FA False SumPrint - Print summary data to .IfW.sum (flag) OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) Wind1VelX +Wind1VelY +Wind1VelZ END of input file (the word "END" must appear in the first 3 columns of this last OutList line) --------------------------------------------------------------------------------------- diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_OLAF.fst b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_OLAF.fst new file mode 100644 index 00000000..0c054e60 --- /dev/null +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT_OLAF.fst @@ -0,0 +1,71 @@ +`------- OpenFAST INPUT FILE ------------------------------------------- +IEA 15 MW offshore reference model monopile configuration +---------------------- SIMULATION CONTROL -------------------------------------- +False Echo - Echo input data to .ech (flag) +"FATAL" AbortLevel - Error level when simulation should abort (string) {"WARNING", "SEVERE", "FATAL"} +300.0 TMax - Total run time (s) +0.005 DT - Recommended module time step (s) +2 InterpOrder - Interpolation order for input/output time history (-) {1=linear, 2=quadratic} +0 NumCrctn - Number of correction iterations (-) {0=explicit calculation, i.e., no corrections} +99999.0 DT_UJac - Time between calls to get Jacobians (s) +1000000.0 UJacSclFact - Scaling factor used in Jacobians (-) +---------------------- FEATURE SWITCHES AND FLAGS ------------------------------ +1 CompElast - Compute structural dynamics (switch) {1=ElastoDyn; 2=ElastoDyn + BeamDyn for blades} +1 CompInflow - Compute inflow wind velocities (switch) {0=still air; 1=InflowWind; 2=external from OpenFOAM} +2 CompAero - Compute aerodynamic loads (switch) {0=None; 1=AeroDyn v14; 2=AeroDyn v15} +1 CompServo - Compute control and electrical-drive dynamics (switch) {0=None; 1=ServoDyn} +1 CompHydro - Compute hydrodynamic loads (switch) {0=None; 1=HydroDyn} +1 CompSub - Compute sub-structural dynamics (switch) {0=None; 1=SubDyn; 2=External Platform MCKF} +0 CompMooring - Compute mooring system (switch) {0=None; 1=MAP++; 2=FEAMooring; 3=MoorDyn; 4=OrcaFlex} +0 CompIce - Compute ice loads (switch) {0=None; 1=IceFloe; 2=IceDyn} +0 MHK - MHK turbine type (switch) {0=Not an MHK turbine; 1=Fixed MHK turbine; 2=Floating MHK turbine} +---------------------- ENVIRONMENTAL CONDITIONS -------------------------------- +9.81 Gravity - Gravitational acceleration (m/s^2) +1.225 AirDens - Air density (kg/m^3) +1025 WtrDens - Water density (kg/m^3) +1.464e-05 KinVisc - Kinematic viscosity of working fluid (m^2/s) +335 SpdSound - Speed of sound in working fluid (m/s) +103500 Patm - Atmospheric pressure (Pa) [used only for an MHK turbine cavitation check] +1700 Pvap - Vapour pressure of working fluid (Pa) [used only for an MHK turbine cavitation check] +30 WtrDpth - Water depth (m) +0 MSL2SWL - Offset between still-water level and mean sea level (m) [positive upward] +---------------------- INPUT FILES --------------------------------------------- +"../IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_ElastoDyn.dat" EDFile - Name of file containing ElastoDyn input parameters (quoted string) +"../IEA-15-240-RWT/IEA-15-240-RWT_BeamDyn.dat" BDBldFile(1) - Name of file containing BeamDyn input parameters for blade 1 (quoted string) +"../IEA-15-240-RWT/IEA-15-240-RWT_BeamDyn.dat" BDBldFile(2) - Name of file containing BeamDyn input parameters for blade 2 (quoted string) +"../IEA-15-240-RWT/IEA-15-240-RWT_BeamDyn.dat" BDBldFile(3) - Name of file containing BeamDyn input parameters for blade 3 (quoted string) +"../IEA-15-240-RWT/IEA-15-240-RWT_InflowFile.dat" InflowFile - Name of file containing inflow wind input parameters (quoted string) +"IEA-15-240-RWT_AeroDyn15.dat" AeroFile - Name of file containing aerodynamic input parameters (quoted string) +"../IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_ServoDyn.dat" ServoFile - Name of file containing control and electrical-drive input parameters (quoted string) +"../IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_HydroDyn.dat" HydroFile - Name of file containing hydrodynamic input parameters (quoted string) +"../IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_SubDyn.dat" SubFile - Name of file containing sub-structural input parameters (quoted string) +"none" MooringFile - Name of file containing mooring system input parameters (quoted string) +"none" IceFile - Name of file containing ice input parameters (quoted string) +---------------------- OUTPUT -------------------------------------------------- +False SumPrint - Print summary data to ".sum" (flag) +10.0 SttsTime - Amount of time between screen status messages (s) +99999.0 ChkptTime - Amount of time between creating checkpoint files for potential restart (s) +"default" DT_Out - Time step for tabular output (s) (or "default") +0.0 TStart - Time to begin tabular output (s) +3 OutFileFmt - Format for tabular (time-marching) output file (switch) {1: text file [.out], 2: binary file [.outb], 3: both} +True TabDelim - Use tab delimiters in text tabular output file? (flag) {uses spaces if false} +"ES10.3E2" OutFmt - Format used for text tabular output, excluding the time channel. Resulting field should be 10 characters. (quoted string) +---------------------- LINEARIZATION ------------------------------------------- +False Linearize - Linearization analysis (flag) +False CalcSteady - Calculate a steady-state periodic operating point before linearization? [unused if Linearize=False] (flag) +3 TrimCase - Controller parameter to be trimmed {1:yaw; 2:torque; 3:pitch} [used only if CalcSteady=True] (-) +0.001 TrimTol - Tolerance for the rotational speed convergence [used only if CalcSteady=True] (-) +0.01 TrimGain - Proportional gain for the rotational speed error (>0) [used only if CalcSteady=True] (rad/(rad/s) for yaw or pitch; Nm/(rad/s) for torque) +0 Twr_Kdmp - Damping factor for the tower [used only if CalcSteady=True] (N/(m/s)) +0 Bld_Kdmp - Damping factor for the blades [used only if CalcSteady=True] (N/(m/s)) +2 NLinTimes - Number of times to linearize (-) [>=1] [unused if Linearize=False] +30.000000, 60.000000 LinTimes - List of times at which to linearize (s) [1 to NLinTimes] [used only when Linearize=True and CalcSteady=False] +1 LinInputs - Inputs included in linearization (switch) {0=none; 1=standard; 2=all module inputs (debug)} [unused if Linearize=False] +1 LinOutputs - Outputs included in linearization (switch) {0=none; 1=from OutList(s); 2=all module outputs (debug)} [unused if Linearize=False] +False LinOutJac - Include full Jacobians in linearization output (for debug) (flag) [unused if Linearize=False; used only if LinInputs=LinOutputs=2] +False LinOutMod - Write module-level linearization output files in addition to output for full system? (flag) [unused if Linearize=False] +---------------------- VISUALIZATION ------------------------------------------ +0 WrVTK - VTK visualization data output: (switch) {0=none; 1=initialization data only; 2=animation} +2 VTK_type - Type of VTK visualization data: (switch) {1=surfaces; 2=basic meshes (lines/points); 3=all meshes (debug)} [unused if WrVTK=0] +False VTK_fields - Write mesh fields to VTK data files? (flag) {true/false} [unused if WrVTK=0] +15.0 VTK_fps - Frame rate for VTK output (frames per second){will use closest integer multiple of DT} [used only if WrVTK=2] diff --git a/docs/source/how_to_contribute_code.rst b/docs/source/how_to_contribute_code.rst index 4426cf4b..b9c6bed1 100644 --- a/docs/source/how_to_contribute_code.rst +++ b/docs/source/how_to_contribute_code.rst @@ -43,3 +43,13 @@ Once you have added or modified code, submit a pull request via the GitHub inter This will automatically go through all of the tests in the repo to make sure everything is functioning properly. The main developers of ROSCO will then merge in the request or provide feedback on how to improve the contribution. +Updating the ROSCO API (Changing Input Files) +--------------------------------------------- +Any API changes should result in the following changes: + +1. Update to the `rosco schema`_. +2. Update to `DISCON writer`_. You can use the `input_descriptions` dictionary to streamline the process. +3. `Document API changes here`_ +4. Update to the `rosco registry`_, which `regenerates the ROSCO_IO using this script`_. + + diff --git a/docs/source/install.rst b/docs/source/install.rst index 40734441..7d21e20a 100644 --- a/docs/source/install.rst +++ b/docs/source/install.rst @@ -23,17 +23,35 @@ Steps for the installation of the complete rosco toolset are: conda create -y --name rosco-env python=3.10 # (Create a new environment named "rosco-env" that contains Python 3.8) conda activate rosco-env # (Activate your "rosco-env" environment) + # Windows users sometimes get an error related to the SSL configuration; in this case, use + # Be sure to execute commands in an anaconda terminal rather than the windows command prompt + conda config --set ssl_verify no + + # Install necessary compilers + conda install -y m2w64-toolchain libpython # windows + conda install compilers # unix + + + # If you intend to use ZeroMQ + brew install zeromq # mac + sudo apt install libzmq3-dev libzmq5 libczmq-dev libczmq4 # linux + 2. Clone and Install the ROSCO toolbox with ROSCO controller .. code-block:: bash git clone https://github.com/NREL/ROSCO.git cd ROSCO - pip install -e . + pip install -e . --no-deps This step creates the rosco controller binary (:code:`libdiscon.so` (Linux), :code:`libdiscon.dylib` (Mac), or :code:`libdisscon.dll` (Windows)`) in the directory :code:`ROSCO/rosco/lib` and installs the python toolbox in the conda environment in the develop mode. +3. If for some reason the pip-based installation does not work, the conda environment can be created using + +.. code-block:: bash + conda env update --file enviroment.yml + pip install -e . --no-deps .. _rosco_controller: diff --git a/pyproject.toml b/pyproject.toml index 5b0f21cf..4031f482 100644 --- a/pyproject.toml +++ b/pyproject.toml @@ -136,9 +136,9 @@ atomic = true #src_paths=isort,test [tool.cibuildwheel] -skip = ["pp*", "cp36-*", "cp37-*", "cp38-*", "*-win32", "*-win_arm64"] #, "*-musllinux*"] +skip = ["pp*", "cp36-*", "cp37-*", "cp38-*", "*-win32", "*-win_arm64", "*-musllinux_aarch64"] build-frontend = { name = "build", args = ["-w","-n"] } -before-build = "pip install setuptools cmake numpy pyzmq cmake-build-extension" +before-build = "pip install setuptools cmake numpy pyzmq cmake-build-extension wheel" build-verbosity = "3" # https://github.com/pdfo/pdfo @@ -149,3 +149,6 @@ environment = { PKG_CONFIG_PATH="c:/opt/64/lib/pkgconfig" } [tool.cibuildwheel.windows] repair-wheel-command = "bash .github/tools/cibw_repair_wheel_command_windows.sh {wheel} {dest_dir}" +# On an Linux Intel runner with qemu installed, build Intel and ARM wheels (aarch64) for Docker. Ignoring: ppc64le s390x +[tool.cibuildwheel.linux] +archs = ["auto", "aarch64"] diff --git a/rosco/controller/src/Functions.f90 b/rosco/controller/src/Functions.f90 index 7fac0bc9..aa411ead 100644 --- a/rosco/controller/src/Functions.f90 +++ b/rosco/controller/src/Functions.f90 @@ -595,7 +595,7 @@ REAL(DbKi) FUNCTION AeroDynTorque(RotSpeed, BldPitch, LocalVar, CntrPar, PerfDat END FUNCTION AeroDynTorque !------------------------------------------------------------------------------------------------------------------------------- - REAL FUNCTION wrap_180(x) + REAL(DbKi) FUNCTION wrap_180(x) ! Function modifies input angle, x, such that -180<=x<=180, preventing windup REAL(DbKi), INTENT(IN) :: x ! angle, degrees @@ -609,7 +609,7 @@ REAL FUNCTION wrap_180(x) END FUNCTION wrap_180 !------------------------------------------------------------------------------------------------------------------------------- - REAL FUNCTION wrap_360(x) + REAL(DbKi) FUNCTION wrap_360(x) ! Function modifies input angle, x, such that 0<=x<=360, preventing windup REAL(DbKi), INTENT(IN) :: x ! angle, degrees diff --git a/rosco/controller/src/ROSCO_IO.f90 b/rosco/controller/src/ROSCO_IO.f90 index a4f44283..c537f9b4 100644 --- a/rosco/controller/src/ROSCO_IO.f90 +++ b/rosco/controller/src/ROSCO_IO.f90 @@ -904,20 +904,20 @@ SUBROUTINE Debug(LocalVar, CntrPar, DebugVar, ErrVar, avrSWAP, RootName, size_av ! Process DebugOutData, LocalVarOutData ! Remove very small numbers that cause ******** outputs DO I = 1,SIZE(DebugOutData) - IF (ABS(DebugOutData(I)) < 1E-99) THEN + IF (ABS(DebugOutData(I)) < 1D-99) THEN DebugOutData(I) = 0 END IF - IF (ABS(DebugOutData(I)) > 1E+99) THEN - DebugOutData(I) = 1E+99 + IF (ABS(DebugOutData(I)) > 1D+99) THEN + DebugOutData(I) = 1D+99 END IF END DO DO I = 1,SIZE(LocalVarOutData) - IF (ABS(LocalVarOutData(I)) < 1E-99) THEN + IF (ABS(LocalVarOutData(I)) < 1D-99) THEN LocalVarOutData(I) = 0 END IF - IF (ABS(LocalVarOutData(I)) > 1E+99) THEN - LocalVarOutData(I) = 1E+99 + IF (ABS(LocalVarOutData(I)) > 1D+99) THEN + LocalVarOutData(I) = 1D+99 END IF END DO @@ -945,4 +945,4 @@ SUBROUTINE Debug(LocalVar, CntrPar, DebugVar, ErrVar, avrSWAP, RootName, size_av ENDIF END SUBROUTINE Debug -END MODULE ROSCO_IO \ No newline at end of file +END MODULE ROSCO_IO diff --git a/rosco/controller/src/SysFiles/SysLLVMLinux.f90 b/rosco/controller/src/SysFiles/SysLLVMLinux.f90 new file mode 100644 index 00000000..0b9a9775 --- /dev/null +++ b/rosco/controller/src/SysFiles/SysLLVMLinux.f90 @@ -0,0 +1,190 @@ +!********************************************************************************************************************************** +! LICENSING +! Copyright (C) 2021 National Renewable Energy Laboratory +! +! This file is part of ROSCO. +! +! Licensed under the Apache License, Version 2.0 (the "License"); +! you may not use this file except in compliance with the License. +! You may obtain a copy of the License at +! +! http://www.apache.org/licenses/LICENSE-2.0 +! +! Unless required by applicable law or agreed to in writing, software +! distributed under the License is distributed on an "AS IS" BASIS, +! WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied. +! See the License for the specific language governing permissions and +! limitations under the License. +!********************************************************************************************************************************** +MODULE SysSubs + + USE ROSCO_Types + USE Constants + + + IMPLICIT NONE + + +! This module contains routines with system-specific logic and references, including all references to the console unit, CU. +! It also contains standard (but not system-specific) routines it uses. +! SysGnuLinux.f90 is specifically for the GNU Fortran (gfortran) compiler on Linux and macOS. + + INTEGER, PARAMETER :: ConRecL = 120 ! The record length for console output. + INTEGER, PARAMETER :: CU = 6 ! The I/O unit for the console. Unit 6 causes ADAMS to crash. + INTEGER, PARAMETER :: MaxWrScrLen = 98 ! The maximum number of characters allowed to be written to a line in WrScr + LOGICAL, PARAMETER :: KBInputOK = .TRUE. ! A flag to tell the program that keyboard input is allowed in the environment. + CHARACTER(*), PARAMETER :: NewLine = ACHAR(10) ! The delimiter for New Lines [ Windows is CHAR(13)//CHAR(10); MAC is CHAR(13); Unix is CHAR(10) {CHAR(13)=\r is a line feed, CHAR(10)=\n is a new line}] + CHARACTER(*), PARAMETER :: OS_Desc = 'LLVM Fortran for Linux' ! Description of the language/OS + CHARACTER( 1), PARAMETER :: PathSep = '/' ! The path separator. + CHARACTER( 1), PARAMETER :: SwChar = '-' ! The switch character for command-line options. + CHARACTER(11), PARAMETER :: UnfForm = 'UNFORMATTED' ! The string to specify unformatted I/O files. + + + CONTAINS +!================================================================================================================= + SUBROUTINE LoadDynamicLib ( DLL, ErrStat, ErrMsg ) + + ! This SUBROUTINE is used to dynamically load a DLL. + + TYPE (ExtDLL_Type), INTENT(INOUT) :: DLL ! The DLL to be loaded. + INTEGER(IntKi), INTENT( OUT) :: ErrStat ! Error status of the operation + CHARACTER(*), INTENT( OUT) :: ErrMsg ! Error message if ErrStat /= ErrID_None + + + !bjj: these are values I found on the web; I have no idea if they actually work... + !bjj: hopefully we can find them pre-defined in a header somewhere + INTEGER(C_INT), PARAMETER :: RTLD_LAZY=1 ! "Perform lazy binding. Only resolve symbols as the code that references them is executed. If the symbol is never referenced, then it is never resolved. (Lazy binding is only performed for function references; references to variables are always immediately bound when the library is loaded.) " + INTEGER(C_INT), PARAMETER :: RTLD_NOW=2 ! "If this value is specified, or the environment variable LD_BIND_NOW is set to a nonempty string, all undefined symbols in the library are resolved before dlopen() returns. If this cannot be done, an error is returned." + INTEGER(C_INT), PARAMETER :: RTLD_GLOBAL=256 ! "The symbols defined by this library will be made available for symbol resolution of subsequently loaded libraries" + INTEGER(C_INT), PARAMETER :: RTLD_LOCAL=0 ! "This is the converse of RTLD_GLOBAL, and the default if neither flag is specified. Symbols defined in this library are not made available to resolve references in subsequently loaded libraries." + + INTERFACE !linux API routines + !bjj see http://linux.die.net/man/3/dlopen + ! and https://developer.apple.com/library/mac/documentation/Darwin/Reference/ManPages/man3/dlopen.3.html + + FUNCTION dlOpen(filename,mode) BIND(C,NAME="dlopen") + ! void *dlopen(const char *filename, int mode); + USE ISO_C_BINDING + IMPLICIT NONE + TYPE(C_PTR) :: dlOpen + CHARACTER(C_CHAR), INTENT(IN) :: filename(*) + INTEGER(C_INT), VALUE :: mode + END FUNCTION + + END INTERFACE + + ErrStat = 0 + ErrMsg = '' + + ! Load the DLL and get the file address: + + DLL%FileAddrX = dlOpen( TRIM(DLL%FileName)//C_NULL_CHAR, RTLD_LAZY ) !the "C_NULL_CHAR" converts the Fortran string to a C-type string (i.e., adds //CHAR(0) to the end) + + IF( .NOT. C_ASSOCIATED(DLL%FileAddrX) ) THEN + ErrStat = -1 + ! WRITE(ErrMsg,'(I2)') BITS_IN_ADDR + ErrMsg = 'The dynamic library '//TRIM(DLL%FileName)//' could not be loaded. Check that the file '// & + 'exists in the specified location and that it is compiled for '//TRIM(ErrMsg)//'-bit applications.' + RETURN + END IF + + ! Get the procedure address: + + CALL LoadDynamicLibProc ( DLL, ErrStat, ErrMsg ) + + RETURN + END SUBROUTINE LoadDynamicLib + !======================================================================= + SUBROUTINE LoadDynamicLibProc ( DLL, ErrStat, ErrMsg ) + + ! This SUBROUTINE is used to dynamically load a procedure from a DLL. + + TYPE (ExtDLL_Type), INTENT(INOUT) :: DLL ! The DLL to be loaded. + INTEGER(IntKi), INTENT( OUT) :: ErrStat ! Error status of the operation + CHARACTER(*), INTENT( OUT) :: ErrMsg ! Error message if ErrStat /= ErrID_None + INTEGER(IntKi) :: i + + + INTERFACE !linux API routines + + !bjj see http://linux.die.net/man/3/dlsym + ! and https://developer.apple.com/library/mac/documentation/Darwin/Reference/ManPages/man3/dlsym.3.html + + FUNCTION dlSym(handle,name) BIND(C,NAME="dlsym") + ! void *dlsym(void *handle, const char *name); + USE ISO_C_BINDING + IMPLICIT NONE + TYPE(C_FUNPTR) :: dlSym ! A function pointer + TYPE(C_PTR), VALUE :: handle + CHARACTER(C_CHAR), INTENT(IN) :: name(*) + END FUNCTION + + END INTERFACE + + ErrStat = ErrID_None + ErrMsg = '' + + do i=1,NWTC_MAX_DLL_PROC + if ( len_trim( DLL%ProcName(i) ) > 0 ) then + + DLL%ProcAddr(i) = dlSym( DLL%FileAddrX, TRIM(DLL%ProcName(i))//C_NULL_CHAR ) !the "C_NULL_CHAR" converts the Fortran string to a C-type string (i.e., adds //CHAR(0) to the end) + + IF(.NOT. C_ASSOCIATED(DLL%ProcAddr(i))) THEN + ErrStat = ErrID_Fatal + ErrMsg = 'The procedure '//TRIM(DLL%ProcName(i))//' in file '//TRIM(DLL%FileName)//' could not be loaded.' + RETURN + END IF + + end if + end do + + RETURN + END SUBROUTINE LoadDynamicLibProc + !======================================================================= + SUBROUTINE FreeDynamicLib ( DLL, ErrStat, ErrMsg ) + + ! This SUBROUTINE is used to free a dynamically loaded DLL (loaded in LoadDynamicLib). + + TYPE (ExtDLL_Type), INTENT(INOUT) :: DLL ! The DLL to be freed. + INTEGER(IntKi), INTENT( OUT) :: ErrStat ! Error status of the operation + CHARACTER(*), INTENT( OUT) :: ErrMsg ! Error message if ErrStat /= ErrID_None + INTEGER(C_INT) :: Success ! Whether or not the call to dlClose was successful + INTEGER(C_INT), PARAMETER :: TRUE = 0 + + !bjj: note that this is not tested. + + INTERFACE !linux API routine + !bjj see http://linux.die.net/man/3/dlclose + ! and https://developer.apple.com/library/mac/documentation/Darwin/Reference/ManPages/man3/dlclose.3.html + + FUNCTION dlClose(handle) BIND(C,NAME="dlclose") + ! int dlclose(void *handle); + USE ISO_C_BINDING + IMPLICIT NONE + INTEGER(C_INT) :: dlClose + TYPE(C_PTR), VALUE :: handle + END FUNCTION + + END INTERFACE + + ! Close the library: + + IF( .NOT. C_ASSOCIATED(DLL%FileAddrX) ) RETURN + Success = dlClose( DLL%FileAddrX ) !The function dlclose() returns 0 on success, and nonzero on error. + + IF ( Success /= TRUE ) THEN !bjj: note that this is not the same as LOGICAL .TRUE. + ErrStat = ErrID_Fatal + ErrMsg = 'The dynamic library could not be freed.' + RETURN + ELSE + ErrStat = ErrID_None + ErrMsg = '' + DLL%FileAddrX = C_NULL_PTR + END IF + + + RETURN + END SUBROUTINE FreeDynamicLib + !======================================================================= + +END MODULE SysSubs diff --git a/rosco/controller/src/SysFiles/SysLLVMWin.f90 b/rosco/controller/src/SysFiles/SysLLVMWin.f90 new file mode 100644 index 00000000..395814aa --- /dev/null +++ b/rosco/controller/src/SysFiles/SysLLVMWin.f90 @@ -0,0 +1,184 @@ +!********************************************************************************************************************************** +! LICENSING +! Copyright (C) 2021 National Renewable Energy Laboratory +! +! This file is part of ROSCO. +! +! Licensed under the Apache License, Version 2.0 (the "License"); +! you may not use this file except in compliance with the License. +! You may obtain a copy of the License at +! +! http://www.apache.org/licenses/LICENSE-2.0 +! +! Unless required by applicable law or agreed to in writing, software +! distributed under the License is distributed on an "AS IS" BASIS, +! WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied. +! See the License for the specific language governing permissions and +! limitations under the License. +!********************************************************************************************************************************** +MODULE SysSubs + + USE ROSCO_Types + USE Constants + + + IMPLICIT NONE + + + + + +! This module contains routines with system-specific logic and references, including all references to the console unit, CU. +! It also contains standard (but not system-specific) routines it uses. +! SysGnuLinux.f90 is specifically for the GNU Fortran (gfortran) compiler on Linux and macOS. + + INTEGER, PARAMETER :: ConRecL = 120 ! The record length for console output. + INTEGER, PARAMETER :: CU = 6 ! The I/O unit for the console. Unit 6 causes ADAMS to crash. + INTEGER, PARAMETER :: MaxWrScrLen = 98 ! The maximum number of characters allowed to be written to a line in WrScr + LOGICAL, PARAMETER :: KBInputOK = .TRUE. ! A flag to tell the program that keyboard input is allowed in the environment. + CHARACTER(*), PARAMETER :: NewLine = ACHAR(10) ! The delimiter for New Lines [ Windows is CHAR(13)//CHAR(10); MAC is CHAR(13); Unix is CHAR(10) {CHAR(13)=\r is a line feed, CHAR(10)=\n is a new line}] + CHARACTER(*), PARAMETER :: OS_Desc = 'LLVM Fortran for Windows' ! Description of the language/OS + CHARACTER( 1), PARAMETER :: PathSep = '\' ! The path separator. + CHARACTER( 1), PARAMETER :: SwChar = '/' ! The switch character for command-line options. + CHARACTER(11), PARAMETER :: UnfForm = 'UNFORMATTED' ! The string to specify unformatted I/O files. + + + CONTAINS +!======================================================================= + SUBROUTINE LoadDynamicLib ( DLL, ErrStat, ErrMsg ) + + ! This SUBROUTINE is used to dynamically load a DLL. + + TYPE (ExtDLL_Type), INTENT(INOUT) :: DLL ! The DLL to be loaded. + INTEGER(IntKi), INTENT( OUT) :: ErrStat ! Error status of the operation + CHARACTER(*), INTENT( OUT) :: ErrMsg ! Error message if ErrStat /= ErrID_None + + INTERFACE ! Definitions of Windows API routines + + !........................... + !bjj: I have been unable to find a solution that works with both IVF and gfortran... + !bjj: note that "Intel Fortran does not support use of STDCALL with BIND(C) at this time" + ! See this link: http://software.intel.com/en-us/articles/replacing-intel-fortran-attributes-with-c-interoperability-features + !bjj: Until this is fixed, Intel uses kernel32.f90 definitions instead of the interface below: + !........................... + + FUNCTION LoadLibrary(lpFileName) BIND(C,NAME='LoadLibraryA') + USE, INTRINSIC :: ISO_C_BINDING + IMPLICIT NONE + !GCC$ ATTRIBUTES STDCALL :: LoadLibrary + INTEGER(C_INTPTR_T) :: LoadLibrary + CHARACTER(KIND=C_CHAR) :: lpFileName(*) + END FUNCTION LoadLibrary + + END INTERFACE + + ErrStat = ErrID_None + ErrMsg = '' + + ! Load the DLL and get the file address: + DLL%FileAddr = LoadLibrary( TRIM(DLL%FileName)//C_NULL_CHAR ) !the "C_NULL_CHAR" converts the Fortran string to a C-type string (i.e., adds //CHAR(0) to the end) + IF ( DLL%FileAddr == INT(0,C_INTPTR_T) ) THEN + ErrStat = ErrID_Fatal + ! WRITE(ErrMsg,'(I2)') BITS_IN_ADDR + ErrMsg = 'The dynamic library '//TRIM(DLL%FileName)//' could not be loaded. Check that the file '// & + 'exists in the specified location and that it is compiled for '//TRIM(ErrMsg)//'-bit applications.' + RETURN + END IF + + ! Get the procedure address: + CALL LoadDynamicLibProc ( DLL, ErrStat, ErrMsg ) + + RETURN + END SUBROUTINE LoadDynamicLib + !======================================================================= + SUBROUTINE LoadDynamicLibProc ( DLL, ErrStat, ErrMsg ) + + ! This SUBROUTINE is used to dynamically load a procedure in a DLL. + + TYPE (ExtDLL_Type), INTENT(INOUT) :: DLL ! The DLL to be loaded. + INTEGER(IntKi), INTENT( OUT) :: ErrStat ! Error status of the operation + CHARACTER(*), INTENT( OUT) :: ErrMsg ! Error message if ErrStat /= ErrID_None + INTEGER(IntKi) :: i + + INTERFACE ! Definitions of Windows API routines + + !........................... + !bjj: I have been unable to find a solution that works with both IVF and gfortran... + !bjj: note that "Intel Fortran does not support use of STDCALL with BIND(C) at this time" + ! See this link: http://software.intel.com/en-us/articles/replacing-intel-fortran-attributes-with-c-interoperability-features + !bjj: Until this is fixed, Intel uses kernel32.f90 definitions instead of the interface below: + !........................... + + FUNCTION GetProcAddress(hModule, lpProcName) BIND(C, NAME='GetProcAddress') + USE, INTRINSIC :: ISO_C_BINDING + IMPLICIT NONE + !GCC$ ATTRIBUTES STDCALL :: GetProcAddress + TYPE(C_FUNPTR) :: GetProcAddress + INTEGER(C_INTPTR_T),VALUE :: hModule + CHARACTER(KIND=C_CHAR) :: lpProcName(*) + END FUNCTION GetProcAddress + + END INTERFACE + + ErrStat = ErrID_None + ErrMsg = '' + + ! Get the procedure addresses: + do i=1,NWTC_MAX_DLL_PROC + if ( len_trim( DLL%ProcName(i) ) > 0 ) then + DLL%ProcAddr(i) = GetProcAddress( DLL%FileAddr, TRIM(DLL%ProcName(i))//C_NULL_CHAR ) !the "C_NULL_CHAR" converts the Fortran string to a C-type string (i.e., adds //CHAR(0) to the end) + IF(.NOT. C_ASSOCIATED(DLL%ProcAddr(i))) THEN + ErrStat = ErrID_Fatal + i - 1 + ErrMsg = 'The procedure '//TRIM(DLL%ProcName(i))//' in file '//TRIM(DLL%FileName)//' could not be loaded.' + RETURN + END IF + end if + end do + + RETURN + END SUBROUTINE LoadDynamicLibProc + !======================================================================= + SUBROUTINE FreeDynamicLib ( DLL, ErrStat, ErrMsg ) + + ! This SUBROUTINE is used to free a dynamically loaded DLL (loaded in LoadDynamicLib). + + TYPE (ExtDLL_Type), INTENT(INOUT) :: DLL ! The DLL to be freed. + INTEGER(IntKi), INTENT( OUT) :: ErrStat ! Error status of the operation + CHARACTER(*), INTENT( OUT) :: ErrMsg ! Error message if ErrStat /= ErrID_None + + ! Local variable: + INTEGER(C_INT) :: Success ! Whether or not the call to FreeLibrary was successful + INTEGER(C_INT), PARAMETER :: FALSE = 0 + + INTERFACE ! Definitions of Windows API routines + + FUNCTION FreeLibrary(hLibModule) BIND(C, NAME='FreeLibrary') + USE, INTRINSIC :: ISO_C_BINDING + IMPLICIT NONE + !GCC$ ATTRIBUTES STDCALL :: FreeLibrary + INTEGER(C_INT) :: FreeLibrary ! BOOL + INTEGER(C_INTPTR_T),VALUE :: hLibModule ! HMODULE hLibModule + END FUNCTION + + END INTERFACE + + ! Free the DLL: + IF ( DLL%FileAddr == INT(0,C_INTPTR_T) ) RETURN + + Success = FreeLibrary( DLL%FileAddr ) !If the function succeeds, the return value is nonzero. If the function fails, the return value is zero. + + IF ( Success == FALSE ) THEN !BJJ: note that this isn't the same as the Fortran LOGICAL .FALSE. + ErrStat = ErrID_Fatal + ErrMsg = 'The dynamic library could not be freed.' + RETURN + ELSE + ErrStat = ErrID_None + ErrMsg = '' + DLL%FileAddr = INT(0,C_INTPTR_T) + END IF + + RETURN + END SUBROUTINE FreeDynamicLib + !======================================================================= + +END MODULE SysSubs diff --git a/rosco/toolbox/ofTools/fast_io/FAST_writer.py b/rosco/toolbox/ofTools/fast_io/FAST_writer.py index 93c26c48..5b1c9c94 100644 --- a/rosco/toolbox/ofTools/fast_io/FAST_writer.py +++ b/rosco/toolbox/ofTools/fast_io/FAST_writer.py @@ -799,6 +799,10 @@ def write_AeroDyn15(self): f.write('====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2]\n') f.write('{:<22d} {:<11} {:}'.format(self.fst_vt['AeroDyn15']['UAMod'], 'UAMod', "- Unsteady Aero Model Switch (switch) {1=Baseline model (Original), 2=Gonzalez's variant (changes in Cn,Cc,Cm), 3=Minnema/Pierce variant (changes in Cc and Cm)} [used only when AFAeroMod=2]\n")) f.write('{!s:<22} {:<11} {:}'.format(self.fst_vt['AeroDyn15']['FLookup'], 'FLookup', "- Flag to indicate whether a lookup for f' will be calculated (TRUE) or whether best-fit exponential equations will be used (FALSE); if FALSE S1-S4 must be provided in airfoil input files (flag) [used only when AFAeroMod=2]\n")) + if 'UAStartRad' in self.fst_vt['AeroDyn15']: + f.write('{:<22} {:<11} {:}'.format(self.fst_vt['AeroDyn15']['UAStartRad'], 'UAStartRad', '- Starting radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2]\n')) + if 'UAEndRad' in self.fst_vt['AeroDyn15']: + f.write('{:<22} {:<11} {:}'.format(self.fst_vt['AeroDyn15']['UAEndRad'], 'UAEndRad', '- Ending radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2]\n')) f.write('====== Airfoil Information =========================================================================\n') f.write('{:<22d} {:<11} {:}'.format(self.fst_vt['AeroDyn15']['AFTabMod'], 'AFTabMod', '- Interpolation method for multiple airfoil tables {1=1D interpolation on AoA (first table only); 2=2D interpolation on AoA and Re; 3=2D interpolation on AoA and UserProp} (-)\n')) f.write('{:<22d} {:<11} {:}'.format(self.fst_vt['AeroDyn15']['InCol_Alfa'], 'InCol_Alfa', '- The column in the airfoil tables that contains the angle of attack (-)\n')) From f52bc4b5cfefecd53d71f6c7162b88e03998f934 Mon Sep 17 00:00:00 2001 From: Abhineet Gupta Date: Fri, 14 Jun 2024 11:32:02 -0600 Subject: [PATCH 2/6] Read damping from beamdyn input files (#349) * Set types on wrap functions * Update IEA-15 inputs * Update installation instructions -- draft * Change to new AF Coords * Fix IEA15 airfoils again * Try latest setup_fortran action * Add UAStart/End location writing * Try intel-classic compiler * Add developer docs about api changes * Try macos-latest in CI * Add support for reading daming from beamdyn blade files (#328) --------- Co-authored-by: dzalkind Co-authored-by: dzalkind <65573423+dzalkind@users.noreply.github.com> --- Examples/Test_Cases/BAR_10/BAR_10.fst | 2 +- rosco/toolbox/turbine.py | 20 ++++++++++++++++---- 2 files changed, 17 insertions(+), 5 deletions(-) diff --git a/Examples/Test_Cases/BAR_10/BAR_10.fst b/Examples/Test_Cases/BAR_10/BAR_10.fst index fab2bcdd..6ea59646 100644 --- a/Examples/Test_Cases/BAR_10/BAR_10.fst +++ b/Examples/Test_Cases/BAR_10/BAR_10.fst @@ -10,7 +10,7 @@ True Echo - Echo input data to .ech (flag) 99999.0 DT_UJac - Time between calls to get Jacobians (s) 1000000.0 UJacSclFact - Scaling factor used in Jacobians (-) ---------------------- FEATURE SWITCHES AND FLAGS ------------------------------ -1 CompElast - Compute structural dynamics (switch) {1=ElastoDyn; 2=ElastoDyn + BeamDyn for blades} +2 CompElast - Compute structural dynamics (switch) {1=ElastoDyn; 2=ElastoDyn + BeamDyn for blades} 1 CompInflow - Compute inflow wind velocities (switch) {0=still air; 1=InflowWind; 2=external from OpenFOAM} 2 CompAero - Compute aerodynamic loads (switch) {0=None; 1=AeroDyn v14; 2=AeroDyn v15} 1 CompServo - Compute control and electrical-drive dynamics (switch) {0=None; 1=ServoDyn} diff --git a/rosco/toolbox/turbine.py b/rosco/toolbox/turbine.py index 73965285..f7cbb727 100644 --- a/rosco/toolbox/turbine.py +++ b/rosco/toolbox/turbine.py @@ -171,10 +171,18 @@ def load_from_fast( # file ed_file = os.path.join(fast.FAST_directory, fast.fst_vt['Fst']['EDFile']) - fast.read_ElastoDyn(ed_file) ed_blade_file = os.path.join(os.path.dirname(ed_file), fast.fst_vt['ElastoDyn']['BldFile1']) - fast.read_ElastoDynBlade(ed_blade_file) + + if fast.fst_vt['Fst']['CompElast'] ==1: + fast.read_ElastoDynBlade(ed_blade_file) + elif fast.fst_vt['Fst']['CompElast'] ==2: + bd_file = os.path.join(fast.FAST_directory, fast.fst_vt['Fst']['BDBldFile(1)']) + fast.read_BeamDyn(bd_file) + bd_blade_file = os.path.join(os.path.dirname(bd_file), fast.fst_vt['BeamDyn']['BldFile']) + fast.read_BeamDynBlade(bd_blade_file) + else: + Warning('No ElastoDyn or BeamDyn files were provided') fast.read_AeroDyn15() @@ -588,8 +596,12 @@ def load_blade_info(self): self.span = r self.chord = chord self.twist = theta - self.bld_flapwise_damp = self.fast.fst_vt['ElastoDynBlade']['BldFlDmp1']/100 - + + if self.fast.fst_vt['Fst']['CompElast'] ==1: + self.bld_flapwise_damp = self.fast.fst_vt['ElastoDynBlade']['BldFlDmp1']/100 + elif self.fast.fst_vt['Fst']['CompElast'] ==2: + self.bld_flapwise_damp = self.fast.fst_vt['BeamDynBlade']['mu5'] + class RotorPerformance(): ''' Class RotorPerformance used to find details from rotor performance From 8b85d7a923b5c2fd99f2178276304fa5ce0d18df Mon Sep 17 00:00:00 2001 From: dzalkind <65573423+dzalkind@users.noreply.github.com> Date: Fri, 14 Jun 2024 11:35:53 -0600 Subject: [PATCH 3/6] Increment version (#358) --- pyproject.toml | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/pyproject.toml b/pyproject.toml index 4031f482..6eba66b4 100644 --- a/pyproject.toml +++ b/pyproject.toml @@ -4,7 +4,7 @@ build-backend = "setuptools.build_meta" [project] name = "rosco" -version = "2.9.2" +version = "2.9.3" description = "A reference open source controller toolset for wind turbine applications." readme = "README.md" requires-python = ">=3.9" From 08ae7cfc97069351112178b0b34873e0ae958b45 Mon Sep 17 00:00:00 2001 From: dzalkind <65573423+dzalkind@users.noreply.github.com> Date: Wed, 10 Jul 2024 13:10:47 -0600 Subject: [PATCH 4/6] Update to latest scipy functions, other input fixes (#363) * Update to latest scipy functions * Update max_torque_rates * sync with new WISDEM syntax * pin to right version of wisdem * Fix max_torque_rates with gearbox ratio --------- Co-authored-by: Garrett Barter --- Examples/Test_Cases/BAR_10/BAR_10_DISCON.IN | 12 +++---- .../DISCON-UMaineSemi.IN | 34 +++++++++---------- Examples/Test_Cases/MHK_RM1/MHK_RM1_DISCON.IN | 14 ++++---- Examples/Test_Cases/NREL-5MW/DISCON.IN | 12 +++---- .../NREL_2p8_127/NREL-2p8-127_DISCON.IN | 12 +++---- Examples/Tune_Cases/BAR.yaml | 2 +- Examples/Tune_Cases/NREL2p8.yaml | 2 +- Examples/Tune_Cases/NREL5MW.yaml | 2 +- Examples/Tune_Cases/NREL5MW_PassThrough.yaml | 2 +- Examples/Tune_Cases/RM1_MHK.yaml | 10 +++--- environment.yml | 2 +- pyproject.toml | 2 +- rosco/toolbox/__init__.py | 2 +- rosco/toolbox/controller.py | 4 +-- rosco/toolbox/inputs/validation.py | 4 +-- rosco/toolbox/turbine.py | 12 +++---- 16 files changed, 64 insertions(+), 64 deletions(-) diff --git a/Examples/Test_Cases/BAR_10/BAR_10_DISCON.IN b/Examples/Test_Cases/BAR_10/BAR_10_DISCON.IN index ebbc56f5..49d1d8be 100644 --- a/Examples/Test_Cases/BAR_10/BAR_10_DISCON.IN +++ b/Examples/Test_Cases/BAR_10/BAR_10_DISCON.IN @@ -1,10 +1,10 @@ ! Controller parameter input file for the BAR_10 wind turbine -! - File written using ROSCO version 2.8.0 controller tuning logic on 01/05/24 +! - File written using ROSCO version 2.9.4 controller tuning logic on 07/01/24 !------- SIMULATION CONTROL ------------------------------------------------------------ 1 ! LoggingLevel - {0: write no debug files, 1: write standard output .dbg-file, 2: LoggingLevel 1 + ROSCO LocalVars (.dbg2) 3: LoggingLevel 2 + complete avrSWAP-array (.dbg3)} 0 ! DT_Out - {Time step to output .dbg* files, or 0 to match sampling period of OpenFAST} -1 ! Ext_Interface - (0 - use standard bladed interface, 1 - Use the extened DLL interface introduced in OpenFAST 3.5.0.) +1 ! Ext_Interface - (0 - use standard bladed interface, 1 - Use the extened DLL interface introduced in OpenFAST 3.5.0.) 0 ! Echo - (0 - no Echo, 1 - Echo input data to .echo) !------- CONTROLLER FLAGS ------------------------------------------------- @@ -53,8 +53,8 @@ !------- BLADE PITCH CONTROL ---------------------------------------------- 30 ! PC_GS_n - Amount of gain-scheduling table entries 0.057899 0.086034 0.108220 0.127602 0.145231 0.161628 0.177110 0.191882 0.205973 0.219605 0.232854 0.245775 0.258317 0.270576 0.282622 0.294421 0.305965 0.317359 0.328547 0.339534 0.350412 0.361066 0.371600 0.382012 0.392231 0.402383 0.412328 0.422200 0.431927 0.441532 ! PC_GS_angles - Gain-schedule table: pitch angles [rad]. --0.017460 -0.014512 -0.012235 -0.010423 -0.008947 -0.007722 -0.006689 -0.005805 -0.005042 -0.004374 -0.003787 -0.003265 -0.002799 -0.002380 -0.002002 -0.001658 -0.001344 -0.001057 -0.000793 -0.000549 -0.000324 -0.000115 0.000080 0.000261 0.000431 0.000590 0.000740 0.000880 0.001013 0.001138 ! PC_GS_KP - Gain-schedule table: pitch controller kp gains [s]. --0.000715 -0.000623 -0.000552 -0.000496 -0.000450 -0.000412 -0.000380 -0.000352 -0.000328 -0.000307 -0.000289 -0.000273 -0.000258 -0.000245 -0.000233 -0.000223 -0.000213 -0.000204 -0.000196 -0.000188 -0.000181 -0.000175 -0.000169 -0.000163 -0.000158 -0.000153 -0.000148 -0.000144 -0.000140 -0.000136 ! PC_GS_KI - Gain-schedule table: pitch controller ki gains [-]. +-0.017426 -0.014498 -0.012232 -0.010428 -0.008956 -0.007733 -0.006701 -0.005818 -0.005054 -0.004387 -0.003799 -0.003276 -0.002810 -0.002390 -0.002011 -0.001666 -0.001352 -0.001064 -0.000799 -0.000554 -0.000328 -0.000118 0.000077 0.000259 0.000430 0.000589 0.000739 0.000881 0.001014 0.001139 ! PC_GS_KP - Gain-schedule table: pitch controller kp gains [s]. +-0.000714 -0.000623 -0.000552 -0.000496 -0.000450 -0.000412 -0.000380 -0.000353 -0.000329 -0.000308 -0.000290 -0.000274 -0.000259 -0.000246 -0.000234 -0.000223 -0.000214 -0.000205 -0.000196 -0.000189 -0.000182 -0.000175 -0.000169 -0.000164 -0.000158 -0.000153 -0.000149 -0.000144 -0.000140 -0.000136 ! PC_GS_KI - Gain-schedule table: pitch controller ki gains [-]. 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 ! PC_GS_KD - Gain-schedule table: pitch controller kd gains 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 ! PC_GS_TF - Gain-schedule table: pitch controller tf gains (derivative filter) 1.570000000000 ! PC_MaxPit - Maximum physical pitch limit, [rad]. @@ -86,7 +86,7 @@ 63892.81326000 ! VS_RtTq - Rated torque, [Nm]. 75.83317000000 ! VS_RefSpd - Rated generator speed [rad/s] 1 ! VS_n - Number of generator PI torque controller gains --2452.07948000 ! VS_KP - Proportional gain for generator PI torque controller [-]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) +-2454.67747000 ! VS_KP - Proportional gain for generator PI torque controller [-]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) -332.357190000 ! VS_KI - Integral gain for generator PI torque controller [s]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) 9.76 ! VS_TSRopt - Power-maximizing region 2 tip-speed-ratio. Only used in VS_ControlMode = 2. 0.314000000000 ! VS_PwrFiltF - Low pass filter on power used to determine generator speed set point. Only used in VS_ControlMode = 3. @@ -113,7 +113,7 @@ 36 26 ! PerfTableSize - Size of rotor performance tables, first number refers to number of blade pitch angles, second number referse to number of tip-speed ratios 60 ! WE_FOPoles_N - Number of first-order system poles used in EKF 3.0000 3.1818 3.3637 3.5455 3.7274 3.9092 4.0911 4.2729 4.4548 4.6366 4.8185 5.0003 5.1822 5.3640 5.5459 5.7277 5.9096 6.0914 6.2732 6.4551 6.6369 6.8188 7.0006 7.1825 7.3643 7.5462 7.7280 7.9099 8.0917 8.2736 8.8311 9.3887 9.9462 10.5038 11.0613 11.6188 12.1764 12.7339 13.2915 13.8490 14.4066 14.9641 15.5217 16.0792 16.6368 17.1943 17.7519 18.3094 18.8670 19.4245 19.9821 20.5396 21.0972 21.6547 22.2123 22.7698 23.3274 23.8849 24.4425 25.0000 ! WE_FOPoles_v - Wind speeds corresponding to first-order system poles [m/s] --0.00972164 -0.01031092 -0.01090020 -0.01148948 -0.01207877 -0.01266805 -0.01325733 -0.01384662 -0.01443590 -0.01502518 -0.01561447 -0.01620375 -0.01679303 -0.01738232 -0.01797160 -0.01856088 -0.01915016 -0.01973945 -0.02032873 -0.02091801 -0.02150730 -0.02209658 -0.02268586 -0.02327515 -0.02386443 -0.02445371 -0.02504300 -0.02563228 -0.02622156 -0.02378670 -0.02062296 -0.02541485 -0.03159105 -0.03849962 -0.04595997 -0.05389417 -0.06225884 -0.07101431 -0.08016995 -0.08970426 -0.09955610 -0.10976762 -0.12028100 -0.13120419 -0.14238799 -0.15383228 -0.16572504 -0.17783697 -0.19011487 -0.20289651 -0.21593424 -0.22919262 -0.24255457 -0.25635133 -0.27049546 -0.28482651 -0.29923376 -0.31380076 -0.32862514 -0.34372726 ! WE_FOPoles - First order system poles [1/s] +-0.00969265 -0.01028018 -0.01086771 -0.01145523 -0.01204276 -0.01263029 -0.01321781 -0.01380534 -0.01439287 -0.01498039 -0.01556792 -0.01615544 -0.01674297 -0.01733050 -0.01791802 -0.01850555 -0.01909308 -0.01968060 -0.02026813 -0.02085566 -0.02144318 -0.02203071 -0.02261823 -0.02320576 -0.02379329 -0.02438081 -0.02496834 -0.02555587 -0.02614339 -0.02379613 -0.02047291 -0.02537932 -0.03151563 -0.03840840 -0.04587537 -0.05382394 -0.06221064 -0.07100937 -0.08011138 -0.08959645 -0.09946249 -0.10970584 -0.12021535 -0.13105665 -0.14226361 -0.15376640 -0.16552312 -0.17764204 -0.19004300 -0.20272586 -0.21577830 -0.22897091 -0.24242644 -0.25613739 -0.27000365 -0.28425482 -0.29866687 -0.31351260 -0.32866968 -0.34414305 ! WE_FOPoles - First order system poles [1/s] !------- YAW CONTROL ------------------------------------------------------ 0.00000 ! Y_uSwitch - Wind speed to switch between Y_ErrThresh. If zero, only the second value of Y_ErrThresh is used [m/s] diff --git a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/DISCON-UMaineSemi.IN b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/DISCON-UMaineSemi.IN index cd58ccf8..a55a49d0 100644 --- a/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/DISCON-UMaineSemi.IN +++ b/Examples/Test_Cases/IEA-15-240-RWT-UMaineSemi/DISCON-UMaineSemi.IN @@ -1,10 +1,10 @@ ! Controller parameter input file for the IEA-15-240-RWT-UMaineSemi wind turbine -! - File written using ROSCO version 2.8.0 controller tuning logic on 01/05/24 +! - File written using ROSCO version 2.9.4 controller tuning logic on 07/01/24 !------- SIMULATION CONTROL ------------------------------------------------------------ 2 ! LoggingLevel - {0: write no debug files, 1: write standard output .dbg-file, 2: LoggingLevel 1 + ROSCO LocalVars (.dbg2) 3: LoggingLevel 2 + complete avrSWAP-array (.dbg3)} 0 ! DT_Out - {Time step to output .dbg* files, or 0 to match sampling period of OpenFAST} -1 ! Ext_Interface - (0 - use standard bladed interface, 1 - Use the extened DLL interface introduced in OpenFAST 3.5.0.) +1 ! Ext_Interface - (0 - use standard bladed interface, 1 - Use the extened DLL interface introduced in OpenFAST 3.5.0.) 0 ! Echo - (0 - no Echo, 1 - Echo input data to .echo) !------- CONTROLLER FLAGS ------------------------------------------------- @@ -52,9 +52,9 @@ !------- BLADE PITCH CONTROL ---------------------------------------------- 30 ! PC_GS_n - Amount of gain-scheduling table entries -0.061311 0.088116 0.108942 0.126990 0.143219 0.158161 0.172040 0.185119 0.197612 0.209635 0.221066 0.232181 0.242992 0.253405 0.263647 0.273567 0.283313 0.292848 0.302185 0.311386 0.320385 0.329291 0.338004 0.346643 0.355108 0.363504 0.371761 0.379937 0.388011 0.395981 ! PC_GS_angles - Gain-schedule table: pitch angles [rad]. --1.206456 -1.044724 -0.911403 -0.799610 -0.704521 -0.622652 -0.551426 -0.488893 -0.433554 -0.384235 -0.340004 -0.300113 -0.263952 -0.231022 -0.200909 -0.173265 -0.147799 -0.124263 -0.102447 -0.082167 -0.063268 -0.045612 -0.029082 -0.013573 0.001008 0.014740 0.027696 0.039940 0.051529 0.062514 ! PC_GS_KP - Gain-schedule table: pitch controller kp gains [s]. --0.125868 -0.113748 -0.103758 -0.095380 -0.088255 -0.082120 -0.076782 -0.072096 -0.067949 -0.064253 -0.060939 -0.057949 -0.055240 -0.052772 -0.050515 -0.048444 -0.046536 -0.044772 -0.043137 -0.041617 -0.040201 -0.038878 -0.037639 -0.036477 -0.035384 -0.034355 -0.033384 -0.032467 -0.031599 -0.030775 ! PC_GS_KI - Gain-schedule table: pitch controller ki gains [-]. +0.062094 0.088628 0.109270 0.127148 0.143223 0.158025 0.171764 0.184722 0.197105 0.209011 0.220338 0.231364 0.242063 0.252399 0.262569 0.272384 0.282068 0.291504 0.300785 0.309890 0.318839 0.327654 0.336324 0.344874 0.353301 0.361612 0.369834 0.377928 0.385970 0.393863 ! PC_GS_angles - Gain-schedule table: pitch angles [rad]. +-1.142777 -0.987724 -0.859824 -0.752519 -0.661205 -0.582556 -0.514107 -0.453995 -0.400785 -0.353352 -0.310803 -0.272422 -0.237625 -0.205931 -0.176944 -0.150331 -0.125812 -0.103149 -0.082139 -0.062607 -0.044403 -0.027396 -0.011472 0.003470 0.017518 0.030750 0.043234 0.055033 0.066202 0.076789 ! PC_GS_KP - Gain-schedule table: pitch controller kp gains [s]. +-0.119556 -0.108083 -0.098619 -0.090679 -0.083922 -0.078102 -0.073038 -0.068590 -0.064652 -0.061143 -0.057994 -0.055154 -0.052579 -0.050234 -0.048089 -0.046120 -0.044306 -0.042629 -0.041074 -0.039629 -0.038282 -0.037024 -0.035845 -0.034740 -0.033700 -0.032721 -0.031797 -0.030924 -0.030098 -0.029315 ! PC_GS_KI - Gain-schedule table: pitch controller ki gains [-]. 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 ! PC_GS_KD - Gain-schedule table: pitch controller kd gains 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 ! PC_GS_TF - Gain-schedule table: pitch controller tf gains (derivative filter) 1.570000000000 ! PC_MaxPit - Maximum physical pitch limit, [rad]. @@ -75,19 +75,19 @@ 0.0 ! IPC_CornerFreqAct - Corner frequency of the first-order actuators model, to induce a phase lag in the IPC signal {0: Disable}, [rad/s] !------- VS TORQUE CONTROL ------------------------------------------------ -96.55000000000 ! VS_GenEff - Generator efficiency mechanical power -> electrical power, [should match the efficiency defined in the generator properties!], [%] -19624046.66639 ! VS_ArSatTq - Above rated generator torque PI control saturation, [Nm] +95.75600000000 ! VS_GenEff - Generator efficiency mechanical power -> electrical power, [should match the efficiency defined in the generator properties!], [%] +19786767.46773 ! VS_ArSatTq - Above rated generator torque PI control saturation, [Nm] 4500000.000000 ! VS_MaxRat - Maximum torque rate (in absolute value) in torque controller, [Nm/s]. -21586451.33303 ! VS_MaxTq - Maximum generator torque in Region 3 (HSS side), [Nm]. +21765444.21450 ! VS_MaxTq - Maximum generator torque in Region 3 (HSS side), [Nm]. 0.000000000000 ! VS_MinTq - Minimum generator torque (HSS side), [Nm]. 0.523600000000 ! VS_MinOMSpd - Minimum generator speed [rad/s] -31393135.82403 ! VS_Rgn2K - Generator torque constant in Region 2 (HSS side). Only used in VS_ControlMode = 1,3 +32413847.90763 ! VS_Rgn2K - Generator torque constant in Region 2 (HSS side). Only used in VS_ControlMode = 1,3 15000000.00000 ! VS_RtPwr - Wind turbine rated power [W] -19624046.66639 ! VS_RtTq - Rated torque, [Nm]. +19786767.46773 ! VS_RtTq - Rated torque, [Nm]. 0.791680000000 ! VS_RefSpd - Rated generator speed [rad/s] 1 ! VS_n - Number of generator PI torque controller gains --37877315.85935 ! VS_KP - Proportional gain for generator PI torque controller [-]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) --4588245.18720 ! VS_KI - Integral gain for generator PI torque controller [s]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) +-35730593.18196 ! VS_KP - Proportional gain for generator PI torque controller [-]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) +-4499370.31680 ! VS_KI - Integral gain for generator PI torque controller [s]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) 9.00 ! VS_TSRopt - Power-maximizing region 2 tip-speed-ratio. Only used in VS_ControlMode = 2. 0.314000000000 ! VS_PwrFiltF - Low pass filter on power used to determine generator speed set point. Only used in VS_ControlMode = 3. @@ -102,18 +102,18 @@ 0.7917 0.7917 ! PRC_GenSpeeds - Array of generator speeds corresponding to PRC_WindSpeeds [rad/s] !------- WIND SPEED ESTIMATOR --------------------------------------------- -120.000 ! WE_BladeRadius - Blade length (distance from hub center to blade tip), [m] +120.970 ! WE_BladeRadius - Blade length (distance from hub center to blade tip), [m] 1 ! WE_CP_n - Amount of parameters in the Cp array 0.0 ! WE_CP - Parameters that define the parameterized CP(lambda) function 0.0 ! WE_Gamma - Adaption gain of the wind speed estimator algorithm [m/rad] 1.0 ! WE_GearboxRatio - Gearbox ratio [>=1], [-] -318628138.00000 ! WE_Jtot - Total drivetrain inertia, including blades, hub and casted generator inertia to LSS, [kg m^2] +312456272.00000 ! WE_Jtot - Total drivetrain inertia, including blades, hub and casted generator inertia to LSS, [kg m^2] 1.225 ! WE_RhoAir - Air density, [kg m^-3] "Cp_Ct_Cq.IEA15MW.txt" ! PerfFileName - File containing rotor performance tables (Cp,Ct,Cq) (absolute path or relative to this file) 36 26 ! PerfTableSize - Size of rotor performance tables, first number refers to number of blade pitch angles, second number referse to number of tip-speed ratios 60 ! WE_FOPoles_N - Number of first-order system poles used in EKF 3.0000 3.2669 3.5338 3.8007 4.0676 4.3345 4.6014 4.8683 5.1352 5.4021 5.6690 5.9359 6.2028 6.4697 6.7366 7.0034 7.2703 7.5372 7.8041 8.0710 8.3379 8.6048 8.8717 9.1386 9.4055 9.6724 9.9393 10.2062 10.4731 10.7400 11.2153 11.6907 12.1660 12.6413 13.1167 13.5920 14.0673 14.5427 15.0180 15.4933 15.9687 16.4440 16.9193 17.3947 17.8700 18.3453 18.8207 19.2960 19.7713 20.2467 20.7220 21.1973 21.6727 22.1480 22.6233 23.0987 23.5740 24.0493 24.5247 25.0000 ! WE_FOPoles_v - Wind speeds corresponding to first-order system poles [m/s] --0.02438353 -0.02655283 -0.02872212 -0.03089141 -0.03306071 -0.03523000 -0.03739930 -0.03956859 -0.04173788 -0.04390718 -0.04607647 -0.04824576 -0.05041506 -0.05258435 -0.05475365 -0.05692294 -0.05909223 -0.06126153 -0.06343082 -0.06560011 -0.06776941 -0.06993870 -0.07210800 -0.07427729 -0.07644658 -0.07861588 -0.08078517 -0.08295446 -0.08512376 -0.08490640 -0.05739531 -0.05967534 -0.06643664 -0.07537721 -0.08537869 -0.09664144 -0.10851650 -0.12137925 -0.13453168 -0.14834459 -0.16280188 -0.17753158 -0.19283401 -0.20862160 -0.22461456 -0.24120058 -0.25817445 -0.27538476 -0.29299882 -0.31103587 -0.32941546 -0.34807902 -0.36693717 -0.38625237 -0.40583167 -0.42579305 -0.44596365 -0.46626113 -0.48675074 -0.50756940 ! WE_FOPoles - First order system poles [1/s] +-0.02567895 -0.02796349 -0.03024803 -0.03253257 -0.03481711 -0.03710166 -0.03938620 -0.04167074 -0.04395528 -0.04623982 -0.04852436 -0.05080890 -0.05309344 -0.05537798 -0.05766253 -0.05994707 -0.06223161 -0.06451615 -0.06680069 -0.06908523 -0.07136977 -0.07365431 -0.07593885 -0.07822339 -0.08050794 -0.08279248 -0.08507702 -0.08736156 -0.08964610 -0.09072643 -0.06009903 -0.06290457 -0.06990800 -0.07913876 -0.08983236 -0.10162611 -0.11417145 -0.12741619 -0.14137334 -0.15599691 -0.17090894 -0.18647049 -0.20252854 -0.21889218 -0.23592237 -0.25309367 -0.27087557 -0.28892640 -0.30743285 -0.32627475 -0.34546793 -0.36504435 -0.38494782 -0.40520553 -0.42575368 -0.44656633 -0.46770980 -0.48900537 -0.51069324 -0.53238692 ! WE_FOPoles - First order system poles [1/s] !------- YAW CONTROL ------------------------------------------------------ 0.00000 ! Y_uSwitch - Wind speed to switch between Y_ErrThresh. If zero, only the second value of Y_ErrThresh is used [m/s] @@ -135,7 +135,7 @@ !------- MINIMUM PITCH SATURATION ------------------------------------------- 60 ! PS_BldPitchMin_N - Number of values in minimum blade pitch lookup table (should equal number of values in PS_WindSpeeds and PS_BldPitchMin) 3.000 3.267 3.534 3.801 4.068 4.334 4.601 4.868 5.135 5.402 5.669 5.936 6.203 6.470 6.737 7.003 7.270 7.537 7.804 8.071 8.338 8.605 8.872 9.139 9.406 9.672 9.939 10.206 10.473 10.740 11.215 11.691 12.166 12.641 13.117 13.592 14.067 14.543 15.018 15.493 15.969 16.444 16.919 17.395 17.870 18.345 18.821 19.296 19.771 20.247 20.722 21.197 21.673 22.148 22.623 23.099 23.574 24.049 24.525 25.000 ! PS_WindSpeeds - Wind speeds corresponding to minimum blade pitch angles [m/s] -0.060 0.060 0.060 0.060 0.060 0.060 0.056 0.051 0.046 0.041 0.034 0.028 0.021 0.014 0.007 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.008 0.022 0.035 0.046 0.053 0.064 0.074 0.084 0.094 0.103 0.112 0.121 0.130 0.139 0.147 0.156 0.164 0.172 0.180 0.189 0.197 0.205 0.212 0.220 0.228 0.236 0.243 0.251 0.259 0.266 0.273 0.281 0.288 0.296 0.303 ! PS_BldPitchMin - Minimum blade pitch angles [rad] +0.060 0.060 0.060 0.060 0.060 0.060 0.056 0.052 0.047 0.041 0.036 0.029 0.022 0.015 0.008 0.001 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.000 0.006 0.021 0.033 0.044 0.053 0.064 0.074 0.084 0.093 0.103 0.112 0.121 0.130 0.138 0.147 0.155 0.163 0.172 0.180 0.188 0.196 0.203 0.211 0.219 0.227 0.234 0.242 0.250 0.257 0.265 0.272 0.279 0.287 0.294 0.301 ! PS_BldPitchMin - Minimum blade pitch angles [rad] !------- SHUTDOWN ----------------------------------------------------------- 0.698100000000 ! SD_MaxPit - Maximum blade pitch angle to initiate shutdown, [rad] @@ -143,7 +143,7 @@ !------- Floating ----------------------------------------------------------- 1 ! Fl_n - Number of Fl_Kp gains in gain scheduling, optional with default of 1 --9.3465 ! Fl_Kp - Nacelle pitching proportional feedback gain [s] +-9.1984 ! Fl_Kp - Nacelle pitching proportional feedback gain [s] 11.2770 ! Fl_U - Wind speeds for scheduling Fl_Kp, optional if Fl_Kp is single value [m/s] !------- FLAP ACTUATION ----------------------------------------------------- diff --git a/Examples/Test_Cases/MHK_RM1/MHK_RM1_DISCON.IN b/Examples/Test_Cases/MHK_RM1/MHK_RM1_DISCON.IN index 322213ff..e23b75b5 100644 --- a/Examples/Test_Cases/MHK_RM1/MHK_RM1_DISCON.IN +++ b/Examples/Test_Cases/MHK_RM1/MHK_RM1_DISCON.IN @@ -1,10 +1,10 @@ ! Controller parameter input file for the MHK_RM1_Floating wind turbine -! - File written using ROSCO version 2.8.0 controller tuning logic on 01/05/24 +! - File written using ROSCO version 2.9.4 controller tuning logic on 07/01/24 !------- SIMULATION CONTROL ------------------------------------------------------------ 2 ! LoggingLevel - {0: write no debug files, 1: write standard output .dbg-file, 2: LoggingLevel 1 + ROSCO LocalVars (.dbg2) 3: LoggingLevel 2 + complete avrSWAP-array (.dbg3)} 0 ! DT_Out - {Time step to output .dbg* files, or 0 to match sampling period of OpenFAST} -1 ! Ext_Interface - (0 - use standard bladed interface, 1 - Use the extened DLL interface introduced in OpenFAST 3.5.0.) +1 ! Ext_Interface - (0 - use standard bladed interface, 1 - Use the extened DLL interface introduced in OpenFAST 3.5.0.) 0 ! Echo - (0 - no Echo, 1 - Echo input data to .echo) !------- CONTROLLER FLAGS ------------------------------------------------- @@ -53,8 +53,8 @@ !------- BLADE PITCH CONTROL ---------------------------------------------- 30 ! PC_GS_n - Amount of gain-scheduling table entries 0.030335 0.049075 0.063610 0.076093 0.087460 0.097196 0.106672 0.115225 0.123634 0.131302 0.139019 0.146056 0.153083 0.159873 0.166338 0.172854 0.178999 0.185046 0.191143 0.196863 0.202559 0.208301 0.213742 0.219137 0.224575 0.229836 0.234972 0.240145 0.245291 0.250200 ! PC_GS_angles - Gain-schedule table: pitch angles [rad]. --0.010178 -0.008780 -0.007625 -0.006655 -0.005829 -0.005116 -0.004495 -0.003950 -0.003467 -0.003036 -0.002650 -0.002301 -0.001984 -0.001696 -0.001432 -0.001190 -0.000966 -0.000760 -0.000568 -0.000390 -0.000225 -0.000069 0.000076 0.000212 0.000340 0.000461 0.000575 0.000682 0.000784 0.000881 ! PC_GS_KP - Gain-schedule table: pitch controller kp gains [s]. --0.005272 -0.004770 -0.004355 -0.004007 -0.003710 -0.003454 -0.003232 -0.003036 -0.002862 -0.002708 -0.002569 -0.002443 -0.002330 -0.002226 -0.002132 -0.002045 -0.001964 -0.001890 -0.001822 -0.001758 -0.001698 -0.001642 -0.001590 -0.001541 -0.001495 -0.001452 -0.001411 -0.001372 -0.001336 -0.001301 ! PC_GS_KI - Gain-schedule table: pitch controller ki gains [-]. +-0.010207 -0.008807 -0.007650 -0.006678 -0.005849 -0.005135 -0.004512 -0.003965 -0.003481 -0.003048 -0.002661 -0.002310 -0.001993 -0.001703 -0.001438 -0.001195 -0.000971 -0.000764 -0.000572 -0.000393 -0.000226 -0.000071 0.000075 0.000212 0.000341 0.000462 0.000576 0.000685 0.000787 0.000884 ! PC_GS_KP - Gain-schedule table: pitch controller kp gains [s]. +-0.005283 -0.004781 -0.004366 -0.004017 -0.003720 -0.003464 -0.003241 -0.003045 -0.002871 -0.002716 -0.002577 -0.002451 -0.002337 -0.002234 -0.002139 -0.002051 -0.001971 -0.001897 -0.001828 -0.001764 -0.001704 -0.001648 -0.001596 -0.001547 -0.001501 -0.001457 -0.001416 -0.001377 -0.001341 -0.001306 ! PC_GS_KI - Gain-schedule table: pitch controller ki gains [-]. 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 ! PC_GS_KD - Gain-schedule table: pitch controller kd gains 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 ! PC_GS_TF - Gain-schedule table: pitch controller tf gains (derivative filter) 1.570000000000 ! PC_MaxPit - Maximum physical pitch limit, [rad]. @@ -86,7 +86,7 @@ 8300.335630000 ! VS_RtTq - Rated torque, [Nm]. 63.81200000000 ! VS_RefSpd - Rated generator speed [rad/s] 1 ! VS_n - Number of generator PI torque controller gains --63.8796200000 ! VS_KP - Proportional gain for generator PI torque controller [-]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) +-63.3401400000 ! VS_KP - Proportional gain for generator PI torque controller [-]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) -84.4329000000 ! VS_KI - Integral gain for generator PI torque controller [s]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) 7.17 ! VS_TSRopt - Power-maximizing region 2 tip-speed-ratio. Only used in VS_ControlMode = 2. 0.314000000000 ! VS_PwrFiltF - Low pass filter on power used to determine generator speed set point. Only used in VS_ControlMode = 3. @@ -113,7 +113,7 @@ 36 26 ! PerfTableSize - Size of rotor performance tables, first number refers to number of blade pitch angles, second number referse to number of tip-speed ratios 60 ! WE_FOPoles_N - Number of first-order system poles used in EKF 0.5000 0.5517 0.6034 0.6552 0.7069 0.7586 0.8103 0.8621 0.9138 0.9655 1.0172 1.0690 1.1207 1.1724 1.2241 1.2759 1.3276 1.3793 1.4310 1.4828 1.5345 1.5862 1.6379 1.6897 1.7414 1.7931 1.8448 1.8966 1.9483 2.0000 2.0333 2.0667 2.1000 2.1333 2.1667 2.2000 2.2333 2.2667 2.3000 2.3333 2.3667 2.4000 2.4333 2.4667 2.5000 2.5333 2.5667 2.6000 2.6333 2.6667 2.7000 2.7333 2.7667 2.8000 2.8333 2.8667 2.9000 2.9333 2.9667 3.0000 ! WE_FOPoles_v - Wind speeds corresponding to first-order system poles [m/s] --0.14364445 -0.15850422 -0.17336400 -0.18822377 -0.20308354 -0.21794331 -0.23280308 -0.24766285 -0.26252262 -0.27738239 -0.29224216 -0.30710193 -0.32196171 -0.33682148 -0.35168125 -0.36654102 -0.38140079 -0.39626056 -0.41112033 -0.42598010 -0.44083987 -0.45569965 -0.47055942 -0.48666545 -0.50602877 -0.52082936 -0.60274133 -0.60720589 -0.60927938 -0.55668516 0.17844923 0.15174296 0.10860051 0.05753679 0.00176535 -0.05812003 -0.11803585 -0.18146508 -0.24666701 -0.31440662 -0.38335107 -0.45418067 -0.52480063 -0.59662243 -0.67000720 -0.74481113 -0.82056059 -0.89753628 -0.97589183 -1.05446405 -1.13345094 -1.21374047 -1.29379323 -1.37507241 -1.45808464 -1.54093580 -1.62426617 -1.70957888 -1.79610923 -1.88140848 ! WE_FOPoles - First order system poles [1/s] +-0.14373366 -0.15860266 -0.17347166 -0.18834066 -0.20320966 -0.21807866 -0.23294766 -0.24781666 -0.26268566 -0.27755466 -0.29242365 -0.30729265 -0.32216165 -0.33703065 -0.35189965 -0.36676865 -0.38163765 -0.39650665 -0.41137565 -0.42624465 -0.44111365 -0.45598265 -0.47085165 -0.48688530 -0.50710708 -0.52286299 -0.60338450 -0.60991074 -0.61241025 -0.55721025 0.17998191 0.15135742 0.10945592 0.05908027 0.00104043 -0.05507169 -0.11824557 -0.18009670 -0.24756868 -0.31240541 -0.38377494 -0.45106439 -0.52304487 -0.59605008 -0.66806086 -0.74501532 -0.81929468 -0.89533886 -0.97582430 -1.05220290 -1.13115451 -1.21410608 -1.29344979 -1.37444765 -1.45900848 -1.54200828 -1.62439937 -1.70996742 -1.79715535 -1.88045193 ! WE_FOPoles - First order system poles [1/s] !------- YAW CONTROL ------------------------------------------------------ 0.00000 ! Y_uSwitch - Wind speed to switch between Y_ErrThresh. If zero, only the second value of Y_ErrThresh is used [m/s] @@ -143,7 +143,7 @@ !------- Floating ----------------------------------------------------------- 1 ! Fl_n - Number of Fl_Kp gains in gain scheduling, optional with default of 1 --0.3999 ! Fl_Kp - Nacelle velocity proportional feedback gain [s] +-0.4009 ! Fl_Kp - Nacelle velocity proportional feedback gain [s] 2.1000 ! Fl_U - Wind speeds for scheduling Fl_Kp, optional if Fl_Kp is single value [m/s] !------- FLAP ACTUATION ----------------------------------------------------- diff --git a/Examples/Test_Cases/NREL-5MW/DISCON.IN b/Examples/Test_Cases/NREL-5MW/DISCON.IN index 0d8024d1..bf86cf78 100644 --- a/Examples/Test_Cases/NREL-5MW/DISCON.IN +++ b/Examples/Test_Cases/NREL-5MW/DISCON.IN @@ -1,10 +1,10 @@ ! Controller parameter input file for the NREL-5MW wind turbine -! - File written using ROSCO version 2.8.0 controller tuning logic on 01/05/24 +! - File written using ROSCO version 2.9.4 controller tuning logic on 07/01/24 !------- SIMULATION CONTROL ------------------------------------------------------------ 1 ! LoggingLevel - {0: write no debug files, 1: write standard output .dbg-file, 2: LoggingLevel 1 + ROSCO LocalVars (.dbg2) 3: LoggingLevel 2 + complete avrSWAP-array (.dbg3)} 0 ! DT_Out - {Time step to output .dbg* files, or 0 to match sampling period of OpenFAST} -1 ! Ext_Interface - (0 - use standard bladed interface, 1 - Use the extened DLL interface introduced in OpenFAST 3.5.0.) +1 ! Ext_Interface - (0 - use standard bladed interface, 1 - Use the extened DLL interface introduced in OpenFAST 3.5.0.) 0 ! Echo - (0 - no Echo, 1 - Echo input data to .echo) !------- CONTROLLER FLAGS ------------------------------------------------- @@ -53,8 +53,8 @@ !------- BLADE PITCH CONTROL ---------------------------------------------- 30 ! PC_GS_n - Amount of gain-scheduling table entries 0.056789 0.084492 0.106018 0.124332 0.140807 0.155903 0.169931 0.183270 0.196062 0.208354 0.220050 0.231503 0.242646 0.253377 0.263967 0.274233 0.284343 0.294292 0.303997 0.313626 0.322957 0.332260 0.341319 0.350368 0.359221 0.368059 0.376700 0.385301 0.393691 0.402050 ! PC_GS_angles - Gain-schedule table: pitch angles [rad]. --0.018995 -0.016672 -0.014787 -0.013228 -0.011916 -0.010797 -0.009831 -0.008989 -0.008248 -0.007592 -0.007006 -0.006480 -0.006005 -0.005574 -0.005182 -0.004822 -0.004492 -0.004187 -0.003906 -0.003644 -0.003402 -0.003175 -0.002963 -0.002765 -0.002579 -0.002404 -0.002239 -0.002083 -0.001936 -0.001797 ! PC_GS_KP - Gain-schedule table: pitch controller kp gains [s]. --0.008388 -0.007514 -0.006805 -0.006218 -0.005725 -0.005304 -0.004940 -0.004624 -0.004345 -0.004098 -0.003878 -0.003680 -0.003501 -0.003339 -0.003192 -0.003056 -0.002932 -0.002817 -0.002712 -0.002613 -0.002522 -0.002437 -0.002357 -0.002283 -0.002212 -0.002147 -0.002085 -0.002026 -0.001971 -0.001918 ! PC_GS_KI - Gain-schedule table: pitch controller ki gains [-]. +-0.019085 -0.016739 -0.014837 -0.013265 -0.011943 -0.010816 -0.009844 -0.008997 -0.008252 -0.007593 -0.007004 -0.006475 -0.005998 -0.005565 -0.005171 -0.004810 -0.004479 -0.004173 -0.003890 -0.003628 -0.003385 -0.003157 -0.002945 -0.002746 -0.002559 -0.002384 -0.002219 -0.002062 -0.001915 -0.001775 ! PC_GS_KP - Gain-schedule table: pitch controller kp gains [s]. +-0.008417 -0.007536 -0.006822 -0.006232 -0.005735 -0.005312 -0.004947 -0.004629 -0.004350 -0.004102 -0.003881 -0.003682 -0.003503 -0.003341 -0.003192 -0.003057 -0.002932 -0.002818 -0.002712 -0.002613 -0.002522 -0.002436 -0.002357 -0.002282 -0.002212 -0.002146 -0.002084 -0.002025 -0.001970 -0.001917 ! PC_GS_KI - Gain-schedule table: pitch controller ki gains [-]. 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 ! PC_GS_KD - Gain-schedule table: pitch controller kd gains 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 ! PC_GS_TF - Gain-schedule table: pitch controller tf gains (derivative filter) 1.570000000000 ! PC_MaxPit - Maximum physical pitch limit, [rad]. @@ -86,7 +86,7 @@ 43093.51876000 ! VS_RtTq - Rated torque, [Nm]. 122.9096700000 ! VS_RefSpd - Rated generator speed [rad/s] 1 ! VS_n - Number of generator PI torque controller gains --657.442080000 ! VS_KP - Proportional gain for generator PI torque controller [-]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) +-654.312360000 ! VS_KP - Proportional gain for generator PI torque controller [-]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) -104.507080000 ! VS_KI - Integral gain for generator PI torque controller [s]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) 7.64 ! VS_TSRopt - Power-maximizing region 2 tip-speed-ratio. Only used in VS_ControlMode = 2. 0.314000000000 ! VS_PwrFiltF - Low pass filter on power used to determine generator speed set point. Only used in VS_ControlMode = 3. @@ -113,7 +113,7 @@ 36 26 ! PerfTableSize - Size of rotor performance tables, first number refers to number of blade pitch angles, second number referse to number of tip-speed ratios 60 ! WE_FOPoles_N - Number of first-order system poles used in EKF 3.0000 3.2897 3.5793 3.8690 4.1586 4.4483 4.7379 5.0276 5.3172 5.6069 5.8966 6.1862 6.4759 6.7655 7.0552 7.3448 7.6345 7.9241 8.2138 8.5034 8.7931 9.0828 9.3724 9.6621 9.9517 10.2414 10.5310 10.8207 11.1103 11.4000 11.8533 12.3067 12.7600 13.2133 13.6667 14.1200 14.5733 15.0267 15.4800 15.9333 16.3867 16.8400 17.2933 17.7467 18.2000 18.6533 19.1067 19.5600 20.0133 20.4667 20.9200 21.3733 21.8267 22.2800 22.7333 23.1867 23.6400 24.0933 24.5467 25.0000 ! WE_FOPoles_v - Wind speeds corresponding to first-order system poles [m/s] --0.01638154 -0.01796321 -0.01954487 -0.02112654 -0.02270820 -0.02428987 -0.02587154 -0.02745320 -0.02903487 -0.03061653 -0.03219820 -0.03377987 -0.03536153 -0.03694320 -0.03852486 -0.04010653 -0.04168820 -0.04326986 -0.04485153 -0.04643319 -0.04801486 -0.04959652 -0.05117819 -0.05275986 -0.05434152 -0.05592319 -0.05758373 -0.05882656 -0.06845507 -0.05992890 -0.05031134 -0.05798636 -0.06840333 -0.08061549 -0.09336590 -0.10698855 -0.12116040 -0.13530722 -0.15025447 -0.16589008 -0.18080009 -0.19651023 -0.21294470 -0.22969213 -0.24540879 -0.26178304 -0.27905964 -0.29706835 -0.31499595 -0.33136688 -0.34832584 -0.36677525 -0.38556416 -0.40554370 -0.42546670 -0.44309547 -0.46062268 -0.47954729 -0.49884696 -0.51943992 ! WE_FOPoles - First order system poles [1/s] +-0.01640352 -0.01798730 -0.01957109 -0.02115488 -0.02273867 -0.02432245 -0.02590624 -0.02749003 -0.02907382 -0.03065761 -0.03224139 -0.03382518 -0.03540897 -0.03699276 -0.03857654 -0.04016033 -0.04174412 -0.04332791 -0.04491170 -0.04649548 -0.04807927 -0.04966306 -0.05124685 -0.05283063 -0.05441442 -0.05599821 -0.05763347 -0.05907205 -0.06912889 -0.05993737 -0.05021616 -0.05780794 -0.06849544 -0.08052122 -0.09351145 -0.10710432 -0.12106730 -0.13547025 -0.15041833 -0.16588021 -0.18135551 -0.19724989 -0.21342206 -0.22970423 -0.24663982 -0.26354532 -0.28064419 -0.29794214 -0.31532544 -0.33332004 -0.35128130 -0.36985759 -0.38827549 -0.40713466 -0.42584061 -0.44509747 -0.46449375 -0.48460700 -0.50475242 -0.52537402 ! WE_FOPoles - First order system poles [1/s] !------- YAW CONTROL ------------------------------------------------------ 0.00000 ! Y_uSwitch - Wind speed to switch between Y_ErrThresh. If zero, only the second value of Y_ErrThresh is used [m/s] diff --git a/Examples/Test_Cases/NREL_2p8_127/NREL-2p8-127_DISCON.IN b/Examples/Test_Cases/NREL_2p8_127/NREL-2p8-127_DISCON.IN index 31d0ed79..46be3ce2 100644 --- a/Examples/Test_Cases/NREL_2p8_127/NREL-2p8-127_DISCON.IN +++ b/Examples/Test_Cases/NREL_2p8_127/NREL-2p8-127_DISCON.IN @@ -1,10 +1,10 @@ ! Controller parameter input file for the NREL-2p8-127 wind turbine -! - File written using ROSCO version 2.8.0 controller tuning logic on 01/05/24 +! - File written using ROSCO version 2.9.4 controller tuning logic on 07/01/24 !------- SIMULATION CONTROL ------------------------------------------------------------ 2 ! LoggingLevel - {0: write no debug files, 1: write standard output .dbg-file, 2: LoggingLevel 1 + ROSCO LocalVars (.dbg2) 3: LoggingLevel 2 + complete avrSWAP-array (.dbg3)} 0 ! DT_Out - {Time step to output .dbg* files, or 0 to match sampling period of OpenFAST} -1 ! Ext_Interface - (0 - use standard bladed interface, 1 - Use the extened DLL interface introduced in OpenFAST 3.5.0.) +1 ! Ext_Interface - (0 - use standard bladed interface, 1 - Use the extened DLL interface introduced in OpenFAST 3.5.0.) 0 ! Echo - (0 - no Echo, 1 - Echo input data to .echo) !------- CONTROLLER FLAGS ------------------------------------------------- @@ -53,8 +53,8 @@ !------- BLADE PITCH CONTROL ---------------------------------------------- 30 ! PC_GS_n - Amount of gain-scheduling table entries 0.075990 0.104503 0.127446 0.147544 0.164940 0.181678 0.197073 0.211624 0.225753 0.238993 0.252021 0.264458 0.276515 0.288229 0.299596 0.310932 0.321646 0.332112 0.342584 0.353105 0.363012 0.373072 0.382733 0.392195 0.401619 0.411107 0.420504 0.429096 0.437752 0.446357 ! PC_GS_angles - Gain-schedule table: pitch angles [rad]. --0.023307 -0.020910 -0.018908 -0.017210 -0.015752 -0.014487 -0.013378 -0.012398 -0.011527 -0.010746 -0.010043 -0.009406 -0.008827 -0.008298 -0.007813 -0.007366 -0.006953 -0.006571 -0.006216 -0.005885 -0.005577 -0.005288 -0.005017 -0.004762 -0.004522 -0.004296 -0.004083 -0.003881 -0.003689 -0.003508 ! PC_GS_KP - Gain-schedule table: pitch controller kp gains [s]. --0.000804 -0.000732 -0.000672 -0.000621 -0.000577 -0.000539 -0.000505 -0.000476 -0.000450 -0.000426 -0.000405 -0.000386 -0.000369 -0.000353 -0.000338 -0.000325 -0.000312 -0.000301 -0.000290 -0.000280 -0.000271 -0.000262 -0.000254 -0.000246 -0.000239 -0.000232 -0.000226 -0.000220 -0.000214 -0.000209 ! PC_GS_KI - Gain-schedule table: pitch controller ki gains [-]. +-0.023241 -0.020868 -0.018883 -0.017197 -0.015748 -0.014490 -0.013386 -0.012410 -0.011542 -0.010763 -0.010062 -0.009426 -0.008848 -0.008320 -0.007835 -0.007388 -0.006976 -0.006594 -0.006238 -0.005908 -0.005599 -0.005310 -0.005038 -0.004783 -0.004543 -0.004317 -0.004103 -0.003901 -0.003709 -0.003527 ! PC_GS_KP - Gain-schedule table: pitch controller kp gains [s]. +-0.000802 -0.000731 -0.000671 -0.000620 -0.000577 -0.000539 -0.000506 -0.000476 -0.000450 -0.000427 -0.000406 -0.000387 -0.000369 -0.000353 -0.000339 -0.000325 -0.000313 -0.000302 -0.000291 -0.000281 -0.000272 -0.000263 -0.000255 -0.000247 -0.000240 -0.000233 -0.000227 -0.000221 -0.000215 -0.000209 ! PC_GS_KI - Gain-schedule table: pitch controller ki gains [-]. 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 ! PC_GS_KD - Gain-schedule table: pitch controller kd gains 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 0.000000 ! PC_GS_TF - Gain-schedule table: pitch controller tf gains (derivative filter) 1.570000000000 ! PC_MaxPit - Maximum physical pitch limit, [rad]. @@ -86,7 +86,7 @@ 24248.54567000 ! VS_RtTq - Rated torque, [Nm]. 122.9096700000 ! VS_RefSpd - Rated generator speed [rad/s] 1 ! VS_n - Number of generator PI torque controller gains --600.450450000 ! VS_KP - Proportional gain for generator PI torque controller [-]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) +-599.338770000 ! VS_KP - Proportional gain for generator PI torque controller [-]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) -85.3230300000 ! VS_KI - Integral gain for generator PI torque controller [s]. (Only used in the transitional 2.5 region if VS_ControlMode =/ 2) 8.25 ! VS_TSRopt - Power-maximizing region 2 tip-speed-ratio. Only used in VS_ControlMode = 2. 0.314000000000 ! VS_PwrFiltF - Low pass filter on power used to determine generator speed set point. Only used in VS_ControlMode = 3. @@ -113,7 +113,7 @@ 30 30 ! PerfTableSize - Size of rotor performance tables, first number refers to number of blade pitch angles, second number referse to number of tip-speed ratios 60 ! WE_FOPoles_N - Number of first-order system poles used in EKF 3.0000 3.2897 3.5793 3.8690 4.1586 4.4483 4.7379 5.0276 5.3172 5.6069 5.8966 6.1862 6.4759 6.7655 7.0552 7.3448 7.6345 7.9241 8.2138 8.5034 8.7931 9.0828 9.3724 9.6621 9.9517 10.2414 10.5310 10.8207 11.1103 11.4000 11.8533 12.3067 12.7600 13.2133 13.6667 14.1200 14.5733 15.0267 15.4800 15.9333 16.3867 16.8400 17.2933 17.7467 18.2000 18.6533 19.1067 19.5600 20.0133 20.4667 20.9200 21.3733 21.8267 22.2800 22.7333 23.1867 23.6400 24.0933 24.5467 25.0000 ! WE_FOPoles_v - Wind speeds corresponding to first-order system poles [m/s] --0.01246409 -0.01366752 -0.01487095 -0.01607438 -0.01727781 -0.01848123 -0.01968466 -0.02088809 -0.02209152 -0.02329495 -0.02449838 -0.02570181 -0.02690524 -0.02810867 -0.02931210 -0.03051553 -0.03171896 -0.03292239 -0.03412582 -0.03532924 -0.03653267 -0.03773610 -0.03893953 -0.04014296 -0.03876534 -0.03527029 -0.03014051 -0.02417865 -0.01714772 -0.00815401 -0.02209033 -0.02677213 -0.03094759 -0.03700125 -0.04188805 -0.04820630 -0.05390840 -0.06043728 -0.06624359 -0.07295380 -0.07986166 -0.08646363 -0.09412176 -0.10174417 -0.10913837 -0.11728247 -0.12497467 -0.13271621 -0.14189107 -0.15083268 -0.15981675 -0.16948290 -0.17870908 -0.18789884 -0.19750668 -0.20786563 -0.21788705 -0.22660607 -0.23612135 -0.24537696 ! WE_FOPoles - First order system poles [1/s] +-0.01260186 -0.01381859 -0.01503532 -0.01625205 -0.01746878 -0.01868551 -0.01990224 -0.02111897 -0.02233570 -0.02355243 -0.02476916 -0.02598590 -0.02720263 -0.02841936 -0.02963609 -0.03085282 -0.03206955 -0.03328628 -0.03450301 -0.03571974 -0.03693647 -0.03815320 -0.03936993 -0.04058667 -0.03922608 -0.03508867 -0.03003198 -0.02417528 -0.01730537 -0.00898539 -0.02245032 -0.02706065 -0.03108854 -0.03712828 -0.04209566 -0.04857003 -0.05395978 -0.06079111 -0.06630809 -0.07261058 -0.07985034 -0.08612180 -0.09374691 -0.10151803 -0.10895439 -0.11680833 -0.12401154 -0.13232357 -0.14130955 -0.14979812 -0.15867841 -0.16925534 -0.17835395 -0.18685622 -0.19682022 -0.20777561 -0.21797608 -0.22670834 -0.23616033 -0.24519119 ! WE_FOPoles - First order system poles [1/s] !------- YAW CONTROL ------------------------------------------------------ 0.00000 ! Y_uSwitch - Wind speed to switch between Y_ErrThresh. If zero, only the second value of Y_ErrThresh is used [m/s] diff --git a/Examples/Tune_Cases/BAR.yaml b/Examples/Tune_Cases/BAR.yaml index bb21281d..bdf96e06 100644 --- a/Examples/Tune_Cases/BAR.yaml +++ b/Examples/Tune_Cases/BAR.yaml @@ -16,7 +16,7 @@ turbine_params: v_rated: 8.27356 # Rated wind speed [m/s] v_max: 25.0 # Cut-out wind speed [m/s], -- Does not need to be exact (JUST ASSUME FOR NOW) max_pitch_rate: 2. # Maximum blade pitch rate [deg/s] - max_torque_rate: 4500000. # Maximum torque rate [Nm/s], {~1/4 VS_RtTq/s} + max_torque_rate: 62000. # Maximum torque rate [Nm/s], {~1/4 VS_RtTq/s} rated_power: 5000000. # Rated Power [W] bld_edgewise_freq: 3.27082 # Blade edgewise first natural frequency [rad/s] bld_flapwise_freq: 2.61601 # Blade flapwise first natural frequency [rad/s] diff --git a/Examples/Tune_Cases/NREL2p8.yaml b/Examples/Tune_Cases/NREL2p8.yaml index c1562a83..3d0af809 100644 --- a/Examples/Tune_Cases/NREL2p8.yaml +++ b/Examples/Tune_Cases/NREL2p8.yaml @@ -63,4 +63,4 @@ controller_params: n_U: 1 omega_flp: 0.0 zeta_flp: 0.0 -turbine_params: {rotor_inertia: 19858184.0, rated_rotor_speed: 1.26711, v_min: 3.0, v_rated: 11.4, v_max: 25.0, max_pitch_rate: 0.1745, max_torque_rate: 1500000.0, rated_power: 2800000.0, bld_edgewise_freq: 8.2831853, bld_flapwise_freq: 0.0, TSR_operational: 0} +turbine_params: {rotor_inertia: 19858184.0, rated_rotor_speed: 1.26711, v_min: 3.0, v_rated: 11.4, v_max: 25.0, max_pitch_rate: 0.1745, max_torque_rate: 22000.0, rated_power: 2800000.0, bld_edgewise_freq: 8.2831853, bld_flapwise_freq: 0.0, TSR_operational: 0} diff --git a/Examples/Tune_Cases/NREL5MW.yaml b/Examples/Tune_Cases/NREL5MW.yaml index 21f5acab..1da5f641 100644 --- a/Examples/Tune_Cases/NREL5MW.yaml +++ b/Examples/Tune_Cases/NREL5MW.yaml @@ -16,7 +16,7 @@ turbine_params: v_rated: 11.4 # Rated wind speed [m/s] v_max: 25.0 # Cut-out wind speed [m/s], -- Does not need to be exact (JUST ASSUME FOR NOW) max_pitch_rate: 0.1745 # Maximum blade pitch rate [rad/s] - max_torque_rate: 1500000. # Maximum torque rate [Nm/s], {~1/4 VS_RtTq/s} + max_torque_rate: 40000. # Maximum torque rate [Nm/s], {~1/4 VS_RtTq/s} rated_power: 5000000. # Rated Power [W] bld_edgewise_freq: 6.2831853 # Blade edgewise first natural frequency [rad/s] bld_flapwise_freq: 0.0 # Blade flapwise first natural frequency [rad/s] diff --git a/Examples/Tune_Cases/NREL5MW_PassThrough.yaml b/Examples/Tune_Cases/NREL5MW_PassThrough.yaml index 7f126785..143e4679 100644 --- a/Examples/Tune_Cases/NREL5MW_PassThrough.yaml +++ b/Examples/Tune_Cases/NREL5MW_PassThrough.yaml @@ -16,7 +16,7 @@ turbine_params: v_rated: 11.4 # Rated wind speed [m/s] v_max: 25.0 # Cut-out wind speed [m/s], -- Does not need to be exact (JUST ASSUME FOR NOW) max_pitch_rate: 0.1745 # Maximum blade pitch rate [rad/s] - max_torque_rate: 1500000. # Maximum torque rate [Nm/s], {~1/4 VS_RtTq/s} + max_torque_rate: 40000. # Maximum torque rate [Nm/s], {~1/4 VS_RtTq/s} rated_power: 5000000. # Rated Power [W] bld_edgewise_freq: 6.2831853 # Blade edgewise first natural frequency [rad/s] bld_flapwise_freq: 0.0 # Blade flapwise first natural frequency [rad/s] diff --git a/Examples/Tune_Cases/RM1_MHK.yaml b/Examples/Tune_Cases/RM1_MHK.yaml index 12b294c2..b4d03cca 100644 --- a/Examples/Tune_Cases/RM1_MHK.yaml +++ b/Examples/Tune_Cases/RM1_MHK.yaml @@ -13,12 +13,12 @@ turbine_params: rotor_inertia: 92169 # Rotor inertia [kg m^2], {Available in Elastodyn .sum file} rated_rotor_speed: 1.204 # 11.5 rpm # Rated rotor speed [rad/s] v_min: 0.5 # Cut-in wind speed [m/s] - v_rated: 2.0 # Rated wind speed [m/s] - v_max: 3.0 # Cut-out wind speed [m/s], -- Does not need to be exact (JUST ASSUME FOR NOW) + v_rated: 2.0 # Rated wind speed [m/s] + v_max: 3.0 # Cut-out wind speed [m/s], -- Does not need to be exact (JUST ASSUME FOR NOW) max_pitch_rate: 0.1745 # Maximum blade pitch rate [rad/s] - max_torque_rate: 1500000. # Maximum torque rate [Nm/s], {~1/4 VS_RtTq/s} - rated_power: 500000 # Rated Power [W] - bld_edgewise_freq: 60.2831853 # Blade edgewise first natural frequency [rad/s] + max_torque_rate: 7800. # Maximum torque rate [Nm/s], {~1/4 VS_RtTq/s} + rated_power: 500000 # Rated Power [W] + bld_edgewise_freq: 60.2831853 # Blade edgewise first natural frequency [rad/s] bld_flapwise_freq: 0.0 # Blade flapwise first natural frequency [rad/s] reynolds_ref: 8e6 # Optional diff --git a/environment.yml b/environment.yml index ab4464f8..fa2bd25e 100644 --- a/environment.yml +++ b/environment.yml @@ -19,4 +19,4 @@ dependencies: - scipy - sphinx_rtd_theme - treon - - wisdem + - wisdem >=3.16 diff --git a/pyproject.toml b/pyproject.toml index 6eba66b4..8b51ab87 100644 --- a/pyproject.toml +++ b/pyproject.toml @@ -4,7 +4,7 @@ build-backend = "setuptools.build_meta" [project] name = "rosco" -version = "2.9.3" +version = "2.9.4" description = "A reference open source controller toolset for wind turbine applications." readme = "README.md" requires-python = ">=3.9" diff --git a/rosco/toolbox/__init__.py b/rosco/toolbox/__init__.py index 3aa708bc..6a29f156 100644 --- a/rosco/toolbox/__init__.py +++ b/rosco/toolbox/__init__.py @@ -3,4 +3,4 @@ __author__ = """Nikhar J. Abbas and Daniel S. Zalkind""" __email__ = 'daniel.zalkind@nrel.gov' -__version__ = '2.9.0' +__version__ = '2.9.4' diff --git a/rosco/toolbox/controller.py b/rosco/toolbox/controller.py index 9b78cce5..f26c67d0 100644 --- a/rosco/toolbox/controller.py +++ b/rosco/toolbox/controller.py @@ -542,8 +542,8 @@ def tune_flap_controller(self,turbine): C1 = np.zeros(len(v_rel)) C2 = np.zeros(len(v_rel)) for i, (v_sec,phi) in enumerate(zip(v_rel, phi_vec)): - C1[i] = integrate.trapz(0.5 * turbine.rho * turbine.chord * v_sec[0]**2 * turbine.span * Kcl * np.cos(phi)) - C2[i] = integrate.trapz(0.5 * turbine.rho * turbine.chord * v_sec[0]**2 * turbine.span * Kcd * np.sin(phi)) + C1[i] = integrate.trapezoid(0.5 * turbine.rho * turbine.chord * v_sec[0]**2 * turbine.span * Kcl * np.cos(phi)) + C2[i] = integrate.trapezoid(0.5 * turbine.rho * turbine.chord * v_sec[0]**2 * turbine.span * Kcd * np.sin(phi)) self.kappa[i]=C1[i]+C2[i] # PI Gains diff --git a/rosco/toolbox/inputs/validation.py b/rosco/toolbox/inputs/validation.py index 8b64e7ac..ade0f3ed 100644 --- a/rosco/toolbox/inputs/validation.py +++ b/rosco/toolbox/inputs/validation.py @@ -1,11 +1,11 @@ import os -from wisdem.inputs import validate_with_defaults +from wisdem.inputs.validation import _validate schema_dir = os.path.dirname(os.path.abspath(__file__)) def load_rosco_yaml(finput): rosco_schema = os.path.join(schema_dir,'toolbox_schema.yaml') - return validate_with_defaults(finput, rosco_schema) + return _validate(finput, rosco_schema, defaults=True) if __name__=='__main__': diff --git a/rosco/toolbox/turbine.py b/rosco/toolbox/turbine.py index f7cbb727..ddf42a04 100644 --- a/rosco/toolbox/turbine.py +++ b/rosco/toolbox/turbine.py @@ -670,9 +670,9 @@ def interp_surface(self,pitch,TSR): ''' # Form the interpolant functions which can look up any arbitrary location on rotor performance surface - interp_fun = interpolate.interp2d( - self.pitch_initial_rad, self.TSR_initial, self.performance_table, kind='cubic') - return interp_fun(pitch,TSR) + interp_fun = interpolate.RectBivariateSpline( + self.pitch_initial_rad, self.TSR_initial, self.performance_table.T) + return np.squeeze(interp_fun(pitch,TSR).T) def interp_gradient(self,pitch,TSR): ''' @@ -691,11 +691,11 @@ def interp_gradient(self,pitch,TSR): [1 x 2] array coresponding to gradient in pitch and TSR directions, respectively ''' # Form the interpolant functions to find gradient at any arbitrary location on rotor performance surface - dCP_beta_interp = interpolate.interp2d(self.pitch_initial_rad, self.TSR_initial, self.gradient_pitch, kind='linear') - dCP_TSR_interp = interpolate.interp2d(self.pitch_initial_rad, self.TSR_initial, self.gradient_TSR, kind='linear') + dCP_beta_interp = interpolate.RectBivariateSpline(self.pitch_initial_rad, self.TSR_initial, self.gradient_pitch.T) + dCP_TSR_interp = interpolate.RectBivariateSpline(self.pitch_initial_rad, self.TSR_initial, self.gradient_TSR.T) # grad.shape output as (2,) numpy array, equivalent to (pitch-direction,TSR-direction) - grad = np.array([dCP_beta_interp(pitch,TSR), dCP_TSR_interp(pitch,TSR)]) + grad = np.array([dCP_beta_interp(pitch,TSR).T, dCP_TSR_interp(pitch,TSR).T]) return np.ndarray.flatten(grad) def plot_performance(self): From 72b2a6a1f581bfe3ec1280671643385fef978d11 Mon Sep 17 00:00:00 2001 From: dzalkind <65573423+dzalkind@users.noreply.github.com> Date: Thu, 11 Jul 2024 08:19:35 -0600 Subject: [PATCH 5/6] Update .readthedocs.yaml (#359) --- .readthedocs.yaml | 5 +++++ 1 file changed, 5 insertions(+) diff --git a/.readthedocs.yaml b/.readthedocs.yaml index 061090c2..2ed53743 100644 --- a/.readthedocs.yaml +++ b/.readthedocs.yaml @@ -10,6 +10,11 @@ build: os: ubuntu-22.04 tools: python: "mambaforge-22.9" + jobs: + # Read the docs needs a couple packages not in the environment file + pre_install: + - conda install -y cmake compilers sphinx sphinxcontrib-bibtex + - conda install sphinx_rtd_theme>=1.3 conda: environment: environment.yml From d6219569302fd4d8f2b8a3a0e4e72f6e9d10160e Mon Sep 17 00:00:00 2001 From: dzalkind <65573423+dzalkind@users.noreply.github.com> Date: Thu, 11 Jul 2024 09:39:27 -0600 Subject: [PATCH 6/6] Update control interface (#366) * Update to latest scipy functions * Update max_torque_rates * minor changes to controller_interface * update scipy version and DISCOn files * sync with new WISDEM syntax * pin to right version of wisdem * Fix max_torque_rates with gearbox ratio --------- Co-authored-by: AthulKrishnaSundarrajan Co-authored-by: Garrett Barter --- rosco/toolbox/control_interface.py | 15 +++++++++++---- 1 file changed, 11 insertions(+), 4 deletions(-) diff --git a/rosco/toolbox/control_interface.py b/rosco/toolbox/control_interface.py index 1a92decf..0e81157e 100644 --- a/rosco/toolbox/control_interface.py +++ b/rosco/toolbox/control_interface.py @@ -74,6 +74,7 @@ def __init__(self, lib_name, param_filename="DISCON.IN", **kwargs): self.char_buffer = 500 self.avr_size = 500 self.sim_name = "simDEBUG" + self.pitch = 0 # option to provid initial blade pitch value # Set kwargs, like DT for k, w in kwargs.items(): @@ -89,7 +90,7 @@ def __init__(self, lib_name, param_filename="DISCON.IN", **kwargs): def init_discon(self): # Initialize - self.pitch = 0 + self.torque = 0 # -- discon self.discon = cdll.LoadLibrary(self.lib_name) @@ -104,9 +105,9 @@ def init_discon(self): self.avrSWAP[26] = 10 # HARD CODE initial wind speed = 10 m/s # Blade pitch initial conditions - self.avrSWAP[3] = 0 * np.deg2rad(1) - self.avrSWAP[32] = 0 * np.deg2rad(1) - self.avrSWAP[33] = 0 * np.deg2rad(1) + self.avrSWAP[3] = self.pitch * np.deg2rad(1) + self.avrSWAP[32] = self.pitch * np.deg2rad(1) + self.avrSWAP[33] = self.pitch * np.deg2rad(1) self.avrSWAP[27] = 1 # IPC @@ -212,6 +213,12 @@ def call_controller(self, turbine_state, end=False): except KeyError: self.avrSWAP[82] = 0 + # pass translational acceleration + try: + self.avrSWAP[52] = turbine_state['FA_Acc'] + except KeyError: + self.avrSWAP[52] = 0 + # call controller self.call_discon()