￥ 测试了不同桨叶片数对拉力/功率之间关系的影响

￥ 测试过程中再次感受到牛顿迭代法的收敛性有多差！

Author: dingzhw

src/00_const.jl

@@ -5,7 +5,7 @@ const ν = 1.46e-4 #运动黏性系数 无量纲
 const g = 9.8 #重力加速度  量纲kg*m*s^-2
 const v_sound = 343.2 #音速 量纲m/s
 const Nro = Int64(2) #Number of rotors
-const Nb = Int64(4)  #Number of blades
+const Nb = Int64(3)  #Number of blades
 const R = 0.8255 #旋翼半径 量纲m
 const chroot = 0.095*R # 桨根弦长
 const airfoil = "NACA0012" # Airfoil
@@ -18,7 +18,7 @@ const Vtip = Ω*R # blade tip velocity
 const αs = -0.0*π/180.0  # 旋翼轴倾角  量纲rad
 const Kβ = 0.0  # 桨叶根部挥舞弹簧刚度 量纲？？？
 const vair = 0.0 # 来流速度 量纲 m/s
-const T = 1000/cos(αs) #飞行器重量 (量纲为kg*m*s^-2)
+const T = 300/cos(αs) #飞行器重量 (量纲为kg*m*s^-2)
 const dpsideg = 10.0  # 方位角步进长度（量纲为deg）
 const betap = 0.0/180*π # Precone
 # const βang0 = 0.0/180*π # 挥舞角初值

src/solfunction.jl

@@ -87,7 +87,7 @@ end
 
         # judge if the indeuce velocity is trimmed
         # rmsind = trvind(vindj[1],vindj[2])
-        if iternum>10
+        if iternum>100
             print("=== Induced Velocity can not be converaged ===\n")
             print("=== Thrust is $(T0) ===\n")
             # print("=== The Total Power need is $(power)===\n")
@@ -107,26 +107,26 @@ end
         vbertmp = vbeui(vall_s, β, dβ, rb)
         vber    = vbertmp
 
-        # calculate the blade flap using 精细数值方法
-        bftmp = bladeflap(β, dβ, ddβ, vber, chord, θ0, θ_lat, θ_lon, dr, rb)
-        if bftmp[1]   # judge if the flap iteration converaged
-            β    = bftmp[2]
-            dβ   = bftmp[3]
-            ddβ  = bftmp[4]
-            β0   = bftmp[5]
-            βlon = bftmp[6]
-            βlat = bftmp[7]
-        end
-
-        # # 使用经验公式求解挥舞
-        # vind_ = lmdui # mean(vdiskind)[3]/(Ω*R)
-        # βtmp = staticbf(θ75, (twist1+twist2), θ_lon, θ_lat, μ_air, abs.(λ_air+vind_))
-        # β = βtmp[1]
-        # dβ = βtmp[2]
-        # ddβ = βtmp[3]
-        # β0 = βtmp[4]
-        # βlon = βtmp[5]
-        # βlat = βtmp[6]
+        # # calculate the blade flap using 精细数值方法
+        # bftmp = bladeflap(β, dβ, ddβ, vber, chord, θ0, θ_lat, θ_lon, dr, rb)
+        # if bftmp[1]   # judge if the flap iteration converaged
+        #     β    = bftmp[2]
+        #     dβ   = bftmp[3]
+        #     ddβ  = bftmp[4]
+        #     β0   = bftmp[5]
+        #     βlon = bftmp[6]
+        #     βlat = bftmp[7]
+        # end
+
+        # 使用经验公式求解挥舞
+        vind_ = lmdui # mean(vdiskind)[3]/(Ω*R)
+        βtmp = staticbf(θ75, (twist1+twist2), θ_lon, θ_lat, μ_air, abs.(λ_air+vind_))
+        β = βtmp[1]
+        dβ = βtmp[2]
+        ddβ = βtmp[3]
+        β0 = βtmp[4]
+        βlon = βtmp[5]
+        βlat = βtmp[6]
 
         # calculate force, moment and power
         rftmp = rotoraero(vber, chord, β, dβ, ddβ, θ0, θ_lat, θ_lon, dr, rb)

test/uitest.jl

@@ -13,13 +13,13 @@ include(pwd()*"//src//rotorforce.jl")
 include(pwd()*"//src//solfunction.jl")
 include(pwd()*"//src//trim.jl")
 
-ttainp = [0.3068026697055875, 0.010809323652109164, -0.03433742775135728]
+ttainp = [0.3068026697055875, 0.0, -0.0]
 trresult = trfm(ttainp[1], ttainp[2], ttainp[3], sol_ui, ntiter)
 show(trresult)
 
 toc()
 
-# cost extra 1139.1348 seconds 
+# cost extra 1139.1348 seconds
 # ---> just make [0.3068026697055875, 0.010809323652109164, -0.03433742775135728]
 # ---> become [0.3071093557471181, -5.913775258831376e-5, -0.0359532799927037]
 # ---> it is not necessary and effecitve for fast analysis