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xfoil.log
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xfoil.log
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===================================================
XFOIL Version 6.99
Copyright (C) 2000 Mark Drela, Harold Youngren
This software comes with ABSOLUTELY NO WARRANTY,
subject to the GNU General Public License.
Caveat computor
===================================================
File xfoil.def not found
QUIT Exit program
.OPER Direct operating point(s)
.MDES Complex mapping design routine
.QDES Surface speed design routine
.GDES Geometry design routine
SAVE f Write airfoil to labeled coordinate file
PSAV f Write airfoil to plain coordinate file
ISAV f Write airfoil to ISES coordinate file
MSAV f Write airfoil to MSES coordinate file
REVE Reverse written-airfoil node ordering
LOAD f Read buffer airfoil from coordinate file
NACA i Set NACA 4,5-digit airfoil and buffer airfoil
INTE Set buffer airfoil by interpolating two airfoils
NORM Buffer airfoil normalization toggle
XYCM rr Change CM reference location, currently 0.25000 0.00000
BEND Display structural properties of current airfoil
PCOP Set current-airfoil panel nodes directly from buffer airfoil points
PANE Set current-airfoil panel nodes ( 160 ) based on curvature
.PPAR Show/change paneling
.PLOP Plotting options
WDEF f Write current-settings file
RDEF f Reread current-settings file
NAME s Specify new airfoil name
NINC Increment name version number
Z Zoom | (available in all menus)
U Unzoom |
XFOIL c> ...............................................
G raphics-enable flag: T
S ize of plot object 10.00"
A spect ratio of plot object 0.5500
P age dimensions 11.00 x 8.50"
M argins from page edges 0.00", 0.00"
F ont size (relative) 0.0150
W indow/screen size fraction 0.8000
B lowup input method: Cursor
O rientation of plot: Landscape
C olor PostScript output? F
Option, Value (or <Return>) c> ...............................................
G raphics-enable flag: F
S ize of plot object 10.00"
A spect ratio of plot object 0.5500
P age dimensions 11.00 x 8.50"
M argins from page edges 0.00", 0.00"
F ont size (relative) 0.0150
W indow/screen size fraction 0.8000
B lowup input method: Cursor
O rientation of plot: Landscape
C olor PostScript output? F
Option, Value (or <Return>) c>
XFOIL c>
XFOIL c>
Labeled airfoil file. Name: EPPLER 908 12%
Number of input coordinate points: 160
Counterclockwise ordering
Max thickness = 0.119999 at x = 0.440
Max camber = 0.027611 at x = 0.669
LE x,y = 0.00002 0.00018 | Chord = 0.99998
TE x,y = 1.00000 0.00000 |
Current airfoil nodes set from buffer airfoil nodes ( 160 )
XFOIL c>
You are working with the buffer airfoil
.GDES c>
Enter flap hinge x location r>
Top surface: y = 0.0655 y/t = 1.0
Bottom surface: y = -0.0124 y/t = 0.0
Enter flap hinge y location (or 999 to specify y/t) r>
Enter flap hinge relative y/t location r>
Flap hinge: x,y = 0.75000 0.02654
Enter flap deflection in degrees (+ down) r>
Top breaks: x,y = 0.75571 0.06468 0.75571 0.06468
Bot breaks: x,y = 0.75171 -0.01229 0.75509 -0.01199
Max thickness = 0.120098 at x = 0.437
Max camber = 0.042778 at x = 0.735
.GDES c>
Current airfoil nodes set from buffer airfoil nodes ( 163 )
.GDES c>
XFOIL c>
.OPERi c> Min Cp will be written to polar save file
.OPERi c>
Polar 1 newly created for accumulation
Airfoil archived with polar: EPPLER 908 12%
Enter polar save filename OR <return> for no file s> plrset nipol,ipol() 7 13
New polar save file available
Enter polar dump filename OR <return> for no file s>
Polar dump file will NOT be written
Polar accumulation enabled
.OPERia c> Calculating unit vorticity distributions ...
plradd ia,ip,cpol 1 538976288 4.40000003E-05
Point added to stored polar 1
plradd ia,ip,cpol 1 538976288 4.40000003E-05
Point written to save file e908_12.dat_f_5.00_cl_1.40.plr
Dump file unspecified or not available
.OPERia c>
Enter filename: e908_12.cp
.OPERia c>
XFOIL c>