XFLR5 Uçak analiz hata veriyor

3

356463

Hectopat
Katılım
27 Temmuz 2020
Mesajlar
4.418
Makaleler
7
Çözümler
40
Airfoil analizini doğru yaptığımı sanıyorum. MH32 kullanıyorum. Kanat oluşturup analiz ettiğimde hata alıyorum.
Konfigrasyonum:

Kod: 
Type 1: Fixed speed



VInf =     15 m/s



3D-Panels/VLM2



Using plane inertia



Mass =   0.000 kg



CoG.x =       0 m



CoG.z =       0 m







B.C. = Dirichlet



Analysis type = Viscous



Ref. dimensions = Planform



Ref. area  =  0.384m²



Ref. span  =  1.600m



Ref. chord =  0.240m



Density =1.225 kg/m3



Viscosity =1.5e-05m²/s







Data points = 0
Kod: 
xflr5 v6.54
05.02.2022  23:07:51

Launching Analysis

Launching the 3D Panel Analysis....
plane
Type 1 - Fixed speed polar

Wings as thin surfaces
Using ring vortices - VLM2
Using Neumann boundary conditions for wings

Density   =       1.225kg/m3
Viscosity =     1.5e-05m²/s

Reference Area   =       0.384m²
Reference length =         1.6m

Counted  494 panel elements

   Mass=       0.000 kg

   ___Center of Gravity Position - Body axis____
    CoG_x=      0.0000 m
    CoG_y=      0.0000 m
    CoG_z=      0.0000 m

   ___Inertia - Body Axis - CoG Origin____
    Ibxx=           0 kg.m²
    Ibyy=           0 kg.m²
    Ibzz=           0 kg.m²
    Ibxz=           0 kg.m²

   Solving the problem...
      Creating the influence matrix...
      Creating the unit RHS vectors...
      Performing LU Matrix decomposition...
      Solving the LU system...
      Time for linear system solve: 0.069 s
      Creating source strengths...
      Calculating doublet strength...
      Calculating aerodynamic coefficients in the far field plane
        Calculating point    0.00°....
        Calculating point   -0.50°....
        Calculating point   -1.00°....
        Calculating point   -1.50°....
        Calculating point   -2.00°....
        Calculating point   -2.50°....
        Calculating point   -3.00°....

      Computing On-Body Speeds...
      Computing Plane for alpha=   0.00°
       Calculating aerodynamic coefficients...
         Calculating wing...Main Wing
           Span pos =     -0.80 m,  Re = 230034,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.79 m,  Re = 230171,  Cl =   0.06 is outside the flight envelope
           Span pos =     -0.78 m,  Re = 230442,  Cl =   0.08 is outside the flight envelope
           Span pos =     -0.77 m,  Re = 230848,  Cl =   0.10 is outside the flight envelope
           Span pos =     -0.74 m,  Re = 231384,  Cl =   0.12 is outside the flight envelope
           Span pos =     -0.72 m,  Re = 232048,  Cl =   0.14 is outside the flight envelope
           Span pos =     -0.69 m,  Re = 232834,  Cl =   0.15 is outside the flight envelope
           Span pos =     -0.65 m,  Re = 233737,  Cl =   0.16 is outside the flight envelope
           Span pos =     -0.61 m,  Re = 234751,  Cl =   0.17 is outside the flight envelope
           Span pos =     -0.57 m,  Re = 235870,  Cl =   0.18 is outside the flight envelope
           Span pos =     -0.52 m,  Re = 237085,  Cl =   0.19 is outside the flight envelope
           Span pos =     -0.46 m,  Re = 238388,  Cl =   0.19 is outside the flight envelope
           Span pos =     -0.41 m,  Re = 239771,  Cl =   0.20 is outside the flight envelope
           Span pos =     -0.35 m,  Re = 241224,  Cl =   0.20 is outside the flight envelope
           Span pos =     -0.29 m,  Re = 242736,  Cl =   0.20 is outside the flight envelope
           Span pos =     -0.23 m,  Re = 244298,  Cl =   0.20 is outside the flight envelope
           Span pos =     -0.16 m,  Re = 245899,  Cl =   0.20 is outside the flight envelope
           Span pos =     -0.10 m,  Re = 247528,  Cl =   0.20 is outside the flight envelope
           Span pos =     -0.03 m,  Re = 249174,  Cl =   0.20 is outside the flight envelope
           Span pos =      0.03 m,  Re = 249174,  Cl =   0.20 is outside the flight envelope
           Span pos =      0.10 m,  Re = 247528,  Cl =   0.20 is outside the flight envelope
           Span pos =      0.16 m,  Re = 245899,  Cl =   0.20 is outside the flight envelope
           Span pos =      0.23 m,  Re = 244298,  Cl =   0.20 is outside the flight envelope
           Span pos =      0.29 m,  Re = 242736,  Cl =   0.20 is outside the flight envelope
           Span pos =      0.35 m,  Re = 241224,  Cl =   0.20 is outside the flight envelope
           Span pos =      0.41 m,  Re = 239771,  Cl =   0.20 is outside the flight envelope
           Span pos =      0.46 m,  Re = 238388,  Cl =   0.19 is outside the flight envelope
           Span pos =      0.52 m,  Re = 237085,  Cl =   0.19 is outside the flight envelope
           Span pos =      0.57 m,  Re = 235870,  Cl =   0.18 is outside the flight envelope
           Span pos =      0.61 m,  Re = 234751,  Cl =   0.17 is outside the flight envelope
           Span pos =      0.65 m,  Re = 233737,  Cl =   0.16 is outside the flight envelope
           Span pos =      0.69 m,  Re = 232834,  Cl =   0.15 is outside the flight envelope
           Span pos =      0.72 m,  Re = 232048,  Cl =   0.14 is outside the flight envelope
           Span pos =      0.74 m,  Re = 231384,  Cl =   0.12 is outside the flight envelope
           Span pos =      0.77 m,  Re = 230848,  Cl =   0.10 is outside the flight envelope
           Span pos =      0.78 m,  Re = 230442,  Cl =   0.08 is outside the flight envelope
           Span pos =      0.79 m,  Re = 230171,  Cl =   0.06 is outside the flight envelope
           Span pos =      0.80 m,  Re = 230034,  Cl =   0.03 is outside the flight envelope

      Computing Plane for alpha=  -0.50°
       Calculating aerodynamic coefficients...
         Calculating wing...Main Wing
           Span pos =     -0.80 m,  Re = 230034,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.79 m,  Re = 230171,  Cl =   0.05 is outside the flight envelope
           Span pos =     -0.78 m,  Re = 230442,  Cl =   0.07 is outside the flight envelope
           Span pos =     -0.77 m,  Re = 230848,  Cl =   0.08 is outside the flight envelope
           Span pos =     -0.74 m,  Re = 231384,  Cl =   0.10 is outside the flight envelope
           Span pos =     -0.72 m,  Re = 232048,  Cl =   0.11 is outside the flight envelope
           Span pos =     -0.69 m,  Re = 232834,  Cl =   0.12 is outside the flight envelope
           Span pos =     -0.65 m,  Re = 233737,  Cl =   0.13 is outside the flight envelope
           Span pos =     -0.61 m,  Re = 234751,  Cl =   0.14 is outside the flight envelope
           Span pos =     -0.57 m,  Re = 235870,  Cl =   0.14 is outside the flight envelope
           Span pos =     -0.52 m,  Re = 237085,  Cl =   0.15 is outside the flight envelope
           Span pos =     -0.46 m,  Re = 238388,  Cl =   0.15 is outside the flight envelope
           Span pos =     -0.41 m,  Re = 239771,  Cl =   0.15 is outside the flight envelope
           Span pos =     -0.35 m,  Re = 241224,  Cl =   0.16 is outside the flight envelope
           Span pos =     -0.29 m,  Re = 242736,  Cl =   0.16 is outside the flight envelope
           Span pos =     -0.23 m,  Re = 244298,  Cl =   0.16 is outside the flight envelope
           Span pos =     -0.16 m,  Re = 245899,  Cl =   0.16 is outside the flight envelope
           Span pos =     -0.10 m,  Re = 247528,  Cl =   0.16 is outside the flight envelope
           Span pos =     -0.03 m,  Re = 249174,  Cl =   0.16 is outside the flight envelope
           Span pos =      0.03 m,  Re = 249174,  Cl =   0.16 is outside the flight envelope
           Span pos =      0.10 m,  Re = 247528,  Cl =   0.16 is outside the flight envelope
           Span pos =      0.16 m,  Re = 245899,  Cl =   0.16 is outside the flight envelope
           Span pos =      0.23 m,  Re = 244298,  Cl =   0.16 is outside the flight envelope
           Span pos =      0.29 m,  Re = 242736,  Cl =   0.16 is outside the flight envelope
           Span pos =      0.35 m,  Re = 241224,  Cl =   0.16 is outside the flight envelope
           Span pos =      0.41 m,  Re = 239771,  Cl =   0.15 is outside the flight envelope
           Span pos =      0.46 m,  Re = 238388,  Cl =   0.15 is outside the flight envelope
           Span pos =      0.52 m,  Re = 237085,  Cl =   0.15 is outside the flight envelope
           Span pos =      0.57 m,  Re = 235870,  Cl =   0.14 is outside the flight envelope
           Span pos =      0.61 m,  Re = 234751,  Cl =   0.14 is outside the flight envelope
           Span pos =      0.65 m,  Re = 233737,  Cl =   0.13 is outside the flight envelope
           Span pos =      0.69 m,  Re = 232834,  Cl =   0.12 is outside the flight envelope
           Span pos =      0.72 m,  Re = 232048,  Cl =   0.11 is outside the flight envelope
           Span pos =      0.74 m,  Re = 231384,  Cl =   0.10 is outside the flight envelope
           Span pos =      0.77 m,  Re = 230848,  Cl =   0.08 is outside the flight envelope
           Span pos =      0.78 m,  Re = 230442,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.79 m,  Re = 230171,  Cl =   0.05 is outside the flight envelope
           Span pos =      0.80 m,  Re = 230034,  Cl =   0.03 is outside the flight envelope

      Computing Plane for alpha=  -1.00°
       Calculating aerodynamic coefficients...
         Calculating wing...Main Wing
           Span pos =     -0.80 m,  Re = 230034,  Cl =   0.02 is outside the flight envelope
           Span pos =     -0.79 m,  Re = 230171,  Cl =   0.04 is outside the flight envelope
           Span pos =     -0.78 m,  Re = 230442,  Cl =   0.05 is outside the flight envelope
           Span pos =     -0.77 m,  Re = 230848,  Cl =   0.06 is outside the flight envelope
           Span pos =     -0.74 m,  Re = 231384,  Cl =   0.08 is outside the flight envelope
           Span pos =     -0.72 m,  Re = 232048,  Cl =   0.08 is outside the flight envelope
           Span pos =     -0.69 m,  Re = 232834,  Cl =   0.09 is outside the flight envelope
           Span pos =     -0.65 m,  Re = 233737,  Cl =   0.10 is outside the flight envelope
           Span pos =     -0.61 m,  Re = 234751,  Cl =   0.10 is outside the flight envelope
           Span pos =     -0.57 m,  Re = 235870,  Cl =   0.10 is outside the flight envelope
           Span pos =     -0.52 m,  Re = 237085,  Cl =   0.11 is outside the flight envelope
           Span pos =     -0.46 m,  Re = 238388,  Cl =   0.11 is outside the flight envelope
           Span pos =     -0.41 m,  Re = 239771,  Cl =   0.11 is outside the flight envelope
           Span pos =     -0.35 m,  Re = 241224,  Cl =   0.11 is outside the flight envelope
           Span pos =     -0.29 m,  Re = 242736,  Cl =   0.11 is outside the flight envelope
           Span pos =     -0.23 m,  Re = 244298,  Cl =   0.11 is outside the flight envelope
           Span pos =     -0.16 m,  Re = 245899,  Cl =   0.12 is outside the flight envelope
           Span pos =     -0.10 m,  Re = 247528,  Cl =   0.11 is outside the flight envelope
           Span pos =     -0.03 m,  Re = 249174,  Cl =   0.11 is outside the flight envelope
           Span pos =      0.03 m,  Re = 249174,  Cl =   0.11 is outside the flight envelope
           Span pos =      0.10 m,  Re = 247528,  Cl =   0.11 is outside the flight envelope
           Span pos =      0.16 m,  Re = 245899,  Cl =   0.12 is outside the flight envelope
           Span pos =      0.23 m,  Re = 244298,  Cl =   0.11 is outside the flight envelope
           Span pos =      0.29 m,  Re = 242736,  Cl =   0.11 is outside the flight envelope
           Span pos =      0.35 m,  Re = 241224,  Cl =   0.11 is outside the flight envelope
           Span pos =      0.41 m,  Re = 239771,  Cl =   0.11 is outside the flight envelope
           Span pos =      0.46 m,  Re = 238388,  Cl =   0.11 is outside the flight envelope
           Span pos =      0.52 m,  Re = 237085,  Cl =   0.11 is outside the flight envelope
           Span pos =      0.57 m,  Re = 235870,  Cl =   0.10 is outside the flight envelope
           Span pos =      0.61 m,  Re = 234751,  Cl =   0.10 is outside the flight envelope
           Span pos =      0.65 m,  Re = 233737,  Cl =   0.10 is outside the flight envelope
           Span pos =      0.69 m,  Re = 232834,  Cl =   0.09 is outside the flight envelope
           Span pos =      0.72 m,  Re = 232048,  Cl =   0.08 is outside the flight envelope
           Span pos =      0.74 m,  Re = 231384,  Cl =   0.08 is outside the flight envelope
           Span pos =      0.77 m,  Re = 230848,  Cl =   0.06 is outside the flight envelope
           Span pos =      0.78 m,  Re = 230442,  Cl =   0.05 is outside the flight envelope
           Span pos =      0.79 m,  Re = 230171,  Cl =   0.04 is outside the flight envelope
           Span pos =      0.80 m,  Re = 230034,  Cl =   0.02 is outside the flight envelope

      Computing Plane for alpha=  -1.50°
       Calculating aerodynamic coefficients...
         Calculating wing...Main Wing
           Span pos =     -0.80 m,  Re = 230034,  Cl =   0.02 is outside the flight envelope
           Span pos =     -0.79 m,  Re = 230171,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.78 m,  Re = 230442,  Cl =   0.04 is outside the flight envelope
           Span pos =     -0.77 m,  Re = 230848,  Cl =   0.04 is outside the flight envelope
           Span pos =     -0.74 m,  Re = 231384,  Cl =   0.05 is outside the flight envelope
           Span pos =     -0.72 m,  Re = 232048,  Cl =   0.06 is outside the flight envelope
           Span pos =     -0.69 m,  Re = 232834,  Cl =   0.06 is outside the flight envelope
           Span pos =     -0.65 m,  Re = 233737,  Cl =   0.06 is outside the flight envelope
           Span pos =     -0.61 m,  Re = 234751,  Cl =   0.06 is outside the flight envelope
           Span pos =     -0.57 m,  Re = 235870,  Cl =   0.07 is outside the flight envelope
           Span pos =     -0.52 m,  Re = 237085,  Cl =   0.07 is outside the flight envelope
           Span pos =     -0.46 m,  Re = 238388,  Cl =   0.07 is outside the flight envelope
           Span pos =     -0.41 m,  Re = 239771,  Cl =   0.07 is outside the flight envelope
           Span pos =     -0.35 m,  Re = 241224,  Cl =   0.07 is outside the flight envelope
           Span pos =     -0.29 m,  Re = 242736,  Cl =   0.07 is outside the flight envelope
           Span pos =     -0.23 m,  Re = 244298,  Cl =   0.07 is outside the flight envelope
           Span pos =     -0.16 m,  Re = 245899,  Cl =   0.07 is outside the flight envelope
           Span pos =     -0.10 m,  Re = 247528,  Cl =   0.07 is outside the flight envelope
           Span pos =     -0.03 m,  Re = 249174,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.03 m,  Re = 249174,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.10 m,  Re = 247528,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.16 m,  Re = 245899,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.23 m,  Re = 244298,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.29 m,  Re = 242736,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.35 m,  Re = 241224,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.41 m,  Re = 239771,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.46 m,  Re = 238388,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.52 m,  Re = 237085,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.57 m,  Re = 235870,  Cl =   0.07 is outside the flight envelope
           Span pos =      0.61 m,  Re = 234751,  Cl =   0.06 is outside the flight envelope
           Span pos =      0.65 m,  Re = 233737,  Cl =   0.06 is outside the flight envelope
           Span pos =      0.69 m,  Re = 232834,  Cl =   0.06 is outside the flight envelope
           Span pos =      0.72 m,  Re = 232048,  Cl =   0.06 is outside the flight envelope
           Span pos =      0.74 m,  Re = 231384,  Cl =   0.05 is outside the flight envelope
           Span pos =      0.77 m,  Re = 230848,  Cl =   0.04 is outside the flight envelope
           Span pos =      0.78 m,  Re = 230442,  Cl =   0.04 is outside the flight envelope
           Span pos =      0.79 m,  Re = 230171,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.80 m,  Re = 230034,  Cl =   0.02 is outside the flight envelope

      Computing Plane for alpha=  -2.00°
       Calculating aerodynamic coefficients...
         Calculating wing...Main Wing
           Span pos =     -0.80 m,  Re = 230034,  Cl =   0.01 is outside the flight envelope
           Span pos =     -0.79 m,  Re = 230171,  Cl =   0.01 is outside the flight envelope
           Span pos =     -0.78 m,  Re = 230442,  Cl =   0.02 is outside the flight envelope
           Span pos =     -0.77 m,  Re = 230848,  Cl =   0.02 is outside the flight envelope
           Span pos =     -0.74 m,  Re = 231384,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.72 m,  Re = 232048,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.69 m,  Re = 232834,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.65 m,  Re = 233737,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.61 m,  Re = 234751,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.57 m,  Re = 235870,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.52 m,  Re = 237085,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.46 m,  Re = 238388,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.41 m,  Re = 239771,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.35 m,  Re = 241224,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.29 m,  Re = 242736,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.23 m,  Re = 244298,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.16 m,  Re = 245899,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.10 m,  Re = 247528,  Cl =   0.03 is outside the flight envelope
           Span pos =     -0.03 m,  Re = 249174,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.03 m,  Re = 249174,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.10 m,  Re = 247528,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.16 m,  Re = 245899,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.23 m,  Re = 244298,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.29 m,  Re = 242736,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.35 m,  Re = 241224,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.41 m,  Re = 239771,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.46 m,  Re = 238388,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.52 m,  Re = 237085,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.57 m,  Re = 235870,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.61 m,  Re = 234751,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.65 m,  Re = 233737,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.69 m,  Re = 232834,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.72 m,  Re = 232048,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.74 m,  Re = 231384,  Cl =   0.03 is outside the flight envelope
           Span pos =      0.77 m,  Re = 230848,  Cl =   0.02 is outside the flight envelope
           Span pos =      0.78 m,  Re = 230442,  Cl =   0.02 is outside the flight envelope
           Span pos =      0.79 m,  Re = 230171,  Cl =   0.01 is outside the flight envelope
           Span pos =      0.80 m,  Re = 230034,  Cl =   0.01 is outside the flight envelope

      Computing Plane for alpha=  -2.50°
       Calculating aerodynamic coefficients...
         Calculating wing...Main Wing
           Span pos =     -0.80 m,  Re = 230034,  Cl =   0.00 is outside the flight envelope
           Span pos =     -0.79 m,  Re = 230171,  Cl =   0.00 is outside the flight envelope
           Span pos =     -0.78 m,  Re = 230442,  Cl =   0.01 is outside the flight envelope
           Span pos =     -0.77 m,  Re = 230848,  Cl =   0.00 is outside the flight envelope
           Span pos =     -0.74 m,  Re = 231384,  Cl =   0.00 is outside the flight envelope
           Span pos =     -0.72 m,  Re = 232048,  Cl =   0.00 is outside the flight envelope
           Span pos =     -0.69 m,  Re = 232834,  Cl =  -0.00 is outside the flight envelope
           Span pos =     -0.65 m,  Re = 233737,  Cl =  -0.00 is outside the flight envelope
           Span pos =     -0.61 m,  Re = 234751,  Cl =  -0.01 is outside the flight envelope
           Span pos =     -0.57 m,  Re = 235870,  Cl =  -0.01 is outside the flight envelope
           Span pos =     -0.52 m,  Re = 237085,  Cl =  -0.01 is outside the flight envelope
           Span pos =     -0.46 m,  Re = 238388,  Cl =  -0.01 is outside the flight envelope
           Span pos =     -0.41 m,  Re = 239771,  Cl =  -0.01 is outside the flight envelope
           Span pos =     -0.35 m,  Re = 241224,  Cl =  -0.02 is outside the flight envelope
           Span pos =     -0.29 m,  Re = 242736,  Cl =  -0.02 is outside the flight envelope
           Span pos =     -0.23 m,  Re = 244298,  Cl =  -0.02 is outside the flight envelope
           Span pos =     -0.16 m,  Re = 245899,  Cl =  -0.02 is outside the flight envelope
           Span pos =     -0.10 m,  Re = 247528,  Cl =  -0.02 is outside the flight envelope
           Span pos =     -0.03 m,  Re = 249174,  Cl =  -0.02 is outside the flight envelope
           Span pos =      0.03 m,  Re = 249174,  Cl =  -0.02 is outside the flight envelope
           Span pos =      0.10 m,  Re = 247528,  Cl =  -0.02 is outside the flight envelope
           Span pos =      0.16 m,  Re = 245899,  Cl =  -0.02 is outside the flight envelope
           Span pos =      0.23 m,  Re = 244298,  Cl =  -0.02 is outside the flight envelope
           Span pos =      0.29 m,  Re = 242736,  Cl =  -0.02 is outside the flight envelope
           Span pos =      0.35 m,  Re = 241224,  Cl =  -0.02 is outside the flight envelope
           Span pos =      0.41 m,  Re = 239771,  Cl =  -0.01 is outside the flight envelope
           Span pos =      0.46 m,  Re = 238388,  Cl =  -0.01 is outside the flight envelope
           Span pos =      0.52 m,  Re = 237085,  Cl =  -0.01 is outside the flight envelope
           Span pos =      0.57 m,  Re = 235870,  Cl =  -0.01 is outside the flight envelope
           Span pos =      0.61 m,  Re = 234751,  Cl =  -0.01 is outside the flight envelope
           Span pos =      0.65 m,  Re = 233737,  Cl =  -0.00 is outside the flight envelope
           Span pos =      0.69 m,  Re = 232834,  Cl =  -0.00 is outside the flight envelope
           Span pos =      0.72 m,  Re = 232048,  Cl =   0.00 is outside the flight envelope
           Span pos =      0.74 m,  Re = 231384,  Cl =   0.00 is outside the flight envelope
           Span pos =      0.77 m,  Re = 230848,  Cl =   0.00 is outside the flight envelope
           Span pos =      0.78 m,  Re = 230442,  Cl =   0.01 is outside the flight envelope
           Span pos =      0.79 m,  Re = 230171,  Cl =   0.00 is outside the flight envelope
           Span pos =      0.80 m,  Re = 230034,  Cl =   0.00 is outside the flight envelope

      Computing Plane for alpha=  -3.00°
       Calculating aerodynamic coefficients...
         Calculating wing...Main Wing
           Span pos =     -0.80 m,  Re = 230034,  Cl =  -0.00 is outside the flight envelope
           Span pos =     -0.79 m,  Re = 230171,  Cl =  -0.01 is outside the flight envelope
           Span pos =     -0.78 m,  Re = 230442,  Cl =  -0.01 is outside the flight envelope
           Span pos =     -0.77 m,  Re = 230848,  Cl =  -0.02 is outside the flight envelope
           Span pos =     -0.74 m,  Re = 231384,  Cl =  -0.02 is outside the flight envelope
           Span pos =     -0.72 m,  Re = 232048,  Cl =  -0.03 is outside the flight envelope
           Span pos =     -0.69 m,  Re = 232834,  Cl =  -0.03 is outside the flight envelope
           Span pos =     -0.65 m,  Re = 233737,  Cl =  -0.04 is outside the flight envelope
           Span pos =     -0.61 m,  Re = 234751,  Cl =  -0.04 is outside the flight envelope
           Span pos =     -0.57 m,  Re = 235870,  Cl =  -0.05 is outside the flight envelope
           Span pos =     -0.52 m,  Re = 237085,  Cl =  -0.05 is outside the flight envelope
           Span pos =     -0.46 m,  Re = 238388,  Cl =  -0.05 is outside the flight envelope
           Span pos =     -0.41 m,  Re = 239771,  Cl =  -0.06 is outside the flight envelope
           Span pos =     -0.35 m,  Re = 241224,  Cl =  -0.06 is outside the flight envelope
           Span pos =     -0.29 m,  Re = 242736,  Cl =  -0.06 is outside the flight envelope
           Span pos =     -0.23 m,  Re = 244298,  Cl =  -0.06 is outside the flight envelope
           Span pos =     -0.16 m,  Re = 245899,  Cl =  -0.06 is outside the flight envelope
           Span pos =     -0.10 m,  Re = 247528,  Cl =  -0.06 is outside the flight envelope
           Span pos =     -0.03 m,  Re = 249174,  Cl =  -0.06 is outside the flight envelope
           Span pos =      0.03 m,  Re = 249174,  Cl =  -0.06 is outside the flight envelope
           Span pos =      0.10 m,  Re = 247528,  Cl =  -0.06 is outside the flight envelope
           Span pos =      0.16 m,  Re = 245899,  Cl =  -0.06 is outside the flight envelope
           Span pos =      0.23 m,  Re = 244298,  Cl =  -0.06 is outside the flight envelope
           Span pos =      0.29 m,  Re = 242736,  Cl =  -0.06 is outside the flight envelope
           Span pos =      0.35 m,  Re = 241224,  Cl =  -0.06 is outside the flight envelope
           Span pos =      0.41 m,  Re = 239771,  Cl =  -0.06 is outside the flight envelope
           Span pos =      0.46 m,  Re = 238388,  Cl =  -0.05 is outside the flight envelope
           Span pos =      0.52 m,  Re = 237085,  Cl =  -0.05 is outside the flight envelope
           Span pos =      0.57 m,  Re = 235870,  Cl =  -0.05 is outside the flight envelope
           Span pos =      0.61 m,  Re = 234751,  Cl =  -0.04 is outside the flight envelope
           Span pos =      0.65 m,  Re = 233737,  Cl =  -0.04 is outside the flight envelope
           Span pos =      0.69 m,  Re = 232834,  Cl =  -0.03 is outside the flight envelope
           Span pos =      0.72 m,  Re = 232048,  Cl =  -0.03 is outside the flight envelope
           Span pos =      0.74 m,  Re = 231384,  Cl =  -0.02 is outside the flight envelope
           Span pos =      0.77 m,  Re = 230848,  Cl =  -0.02 is outside the flight envelope
           Span pos =      0.78 m,  Re = 230442,  Cl =  -0.01 is outside the flight envelope
           Span pos =      0.79 m,  Re = 230171,  Cl =  -0.01 is outside the flight envelope
           Span pos =      0.80 m,  Re = 230034,  Cl =  -0.00 is outside the flight envelope


Panel Analysis completed ... Errors encountered
Nerede hata yapıyorum? Hatanın çözülmesi için hangi dosyaları paylaşmalıyım sizle?
@SideWinder @Jira @Çağlar0707
 
356463 dedi:
Airfoil analizini doğru yaptığımı sanıyorum. MH32 kullanıyorum. Kanat oluşturup analiz ettiğimde hata alıyorum.
Konfigrasyonum:

Kod: 
Type 1: Fixed speed.

VInf = 15 m/s

3D-Panels/VLM2

Using plane inertia.

Mass = 0.000 kg.

CoG.x = 0 m

CoG.z = 0 m

B.C. = Dirichlet.

Analysis type = Viscous.

Ref. dimensions = Planform.

Ref. area = 0.384m²

Ref. span = 1.600m

Ref. chord = 0.240m

Density =1.225 kg/m3

Viscosity =1.5e-05m²/s

Data points = 0
Kod: 
xflr5 v6.54
05.02.2022 23:07:51

Launching Analysis.

Launching the 3D Panel Analysis....
plane.
Type 1 - Fixed speed polar.

Wings as thin surfaces.
Using ring vortices - VLM2.
Using Neumann boundary conditions for wings.

Density = 1.225kg/m3
Viscosity = 1.5e-05m²/s

Reference Area = 0.384m²
Reference length = 1.6m

Counted 494 panel elements.

 Mass= 0.000 kg.

 ___Center of Gravity Position - Body axis____.
 CoG_x= 0.0000 m
 CoG_y= 0.0000 m
 CoG_z= 0.0000 m

 ___Inertia - Body Axis - CoG Origin____.
 Ibxx= 0 kg.m²
 Ibyy= 0 kg.m²
 Ibzz= 0 kg.m²
 Ibxz= 0 kg.m²

 Solving the problem...
 Creating the influence matrix...
 Creating the unit RHS vectors...
 Performing LU Matrix decomposition...
 Solving the LU system...
 Time for linear system solve: 0.069 s
 Creating source strengths...
 Calculating doublet strength...
 Calculating aerodynamic coefficients in the far field plane.
 Calculating point 0.00°....
 Calculating point -0.50°....
 Calculating point -1.00°....
 Calculating point -1.50°....
 Calculating point -2.00°....
 Calculating point -2.50°....
 Calculating point -3.00°....

 Computing On-Body Speeds...
 Computing Plane for alpha= 0.00°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.08 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.10 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.12 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.14 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = 0.15 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = 0.17 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = 0.18 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = 0.19 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = 0.19 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = 0.19 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = 0.19 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = 0.18 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = 0.17 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = 0.15 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.14 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.12 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.10 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.08 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.03 is outside the flight envelope.

 Computing Plane for alpha= -0.50°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.05 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.08 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.10 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = 0.12 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = 0.13 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = 0.14 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = 0.14 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = 0.15 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = 0.15 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = 0.15 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = 0.15 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = 0.15 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = 0.15 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = 0.14 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = 0.14 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = 0.13 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = 0.12 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.10 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.08 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.05 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.03 is outside the flight envelope.

 Computing Plane for alpha= -1.00°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.02 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.04 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.05 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.08 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.08 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = 0.09 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = 0.10 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = 0.10 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = 0.10 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = 0.12 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = 0.12 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = 0.10 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = 0.10 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = 0.10 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = 0.09 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.08 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.08 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.05 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.04 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.02 is outside the flight envelope.

 Computing Plane for alpha= -1.50°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.02 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.04 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.04 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.05 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.05 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.04 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.04 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.02 is outside the flight envelope.

 Computing Plane for alpha= -2.00°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.01 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.01 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.02 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.02 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.02 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.02 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.01 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.01 is outside the flight envelope.

 Computing Plane for alpha= -2.50°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.00 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.00 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.01 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.00 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.00 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.00 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = -0.00 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = -0.00 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = -0.00 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = -0.00 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.00 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.00 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.00 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.01 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.00 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.00 is outside the flight envelope.

 Computing Plane for alpha= -3.00°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = -0.00 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = -0.03 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = -0.03 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = -0.04 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = -0.04 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = -0.05 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = -0.05 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = -0.05 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = -0.05 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = -0.05 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = -0.05 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = -0.04 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = -0.04 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = -0.03 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = -0.03 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = -0.00 is outside the flight envelope.

Panel Analysis completed ... Errors encountered
Nerede hata yapıyorum? Hatanın çözülmesi için hangi dosyaları paylaşmalıyım sizle?
@SideWinder @Jira @Çağlar0707
Genişletmek için tıkla...

Hocam, gördüğün reynolds numberlarında hata alıyorsun, bu sorundan kurtulmak için xfoil Direct analizden bu reynolds numaralarını tanımlayıp analiz etmen gerekiyor sonra wing üzerinde bu değerleri çalışabilirsin.

356463 dedi:
Airfoil analizini doğru yaptığımı sanıyorum. MH32 kullanıyorum. Kanat oluşturup analiz ettiğimde hata alıyorum.
Konfigrasyonum:

Kod: 
Type 1: Fixed speed.

VInf = 15 m/s

3D-Panels/VLM2

Using plane inertia.

Mass = 0.000 kg.

CoG.x = 0 m

CoG.z = 0 m

B.C. = Dirichlet.

Analysis type = Viscous.

Ref. dimensions = Planform.

Ref. area = 0.384m²

Ref. span = 1.600m

Ref. chord = 0.240m

Density =1.225 kg/m3

Viscosity =1.5e-05m²/s

Data points = 0
Kod: 
xflr5 v6.54
05.02.2022 23:07:51

Launching Analysis.

Launching the 3D Panel Analysis....
plane.
Type 1 - Fixed speed polar.

Wings as thin surfaces.
Using ring vortices - VLM2.
Using Neumann boundary conditions for wings.

Density = 1.225kg/m3
Viscosity = 1.5e-05m²/s

Reference Area = 0.384m²
Reference length = 1.6m

Counted 494 panel elements.

 Mass= 0.000 kg.

 ___Center of Gravity Position - Body axis____.
 CoG_x= 0.0000 m
 CoG_y= 0.0000 m
 CoG_z= 0.0000 m

 ___Inertia - Body Axis - CoG Origin____.
 Ibxx= 0 kg.m²
 Ibyy= 0 kg.m²
 Ibzz= 0 kg.m²
 Ibxz= 0 kg.m²

 Solving the problem...
 Creating the influence matrix...
 Creating the unit RHS vectors...
 Performing LU Matrix decomposition...
 Solving the LU system...
 Time for linear system solve: 0.069 s
 Creating source strengths...
 Calculating doublet strength...
 Calculating aerodynamic coefficients in the far field plane.
 Calculating point 0.00°....
 Calculating point -0.50°....
 Calculating point -1.00°....
 Calculating point -1.50°....
 Calculating point -2.00°....
 Calculating point -2.50°....
 Calculating point -3.00°....

 Computing On-Body Speeds...
 Computing Plane for alpha= 0.00°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.08 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.10 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.12 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.14 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = 0.15 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = 0.17 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = 0.18 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = 0.19 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = 0.19 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = 0.20 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = 0.20 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = 0.19 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = 0.19 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = 0.18 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = 0.17 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = 0.15 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.14 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.12 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.10 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.08 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.03 is outside the flight envelope.

 Computing Plane for alpha= -0.50°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.05 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.08 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.10 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = 0.12 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = 0.13 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = 0.14 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = 0.14 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = 0.15 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = 0.15 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = 0.15 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = 0.16 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = 0.16 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = 0.15 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = 0.15 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = 0.15 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = 0.14 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = 0.14 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = 0.13 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = 0.12 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.10 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.08 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.05 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.03 is outside the flight envelope.

 Computing Plane for alpha= -1.00°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.02 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.04 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.05 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.08 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.08 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = 0.09 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = 0.10 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = 0.10 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = 0.10 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = 0.12 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = 0.11 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = 0.12 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = 0.11 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = 0.10 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = 0.10 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = 0.10 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = 0.09 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.08 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.08 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.05 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.04 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.02 is outside the flight envelope.

 Computing Plane for alpha= -1.50°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.02 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.04 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.04 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.05 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = 0.06 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = 0.07 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = 0.07 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.06 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.05 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.04 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.04 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.02 is outside the flight envelope.

 Computing Plane for alpha= -2.00°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.01 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.01 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.02 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.02 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = 0.03 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.03 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.02 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.02 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.01 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.01 is outside the flight envelope.

 Computing Plane for alpha= -2.50°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = 0.00 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = 0.00 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = 0.01 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = 0.00 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = 0.00 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = 0.00 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = -0.00 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = -0.00 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = -0.00 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = -0.00 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = 0.00 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = 0.00 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = 0.00 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = 0.01 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = 0.00 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = 0.00 is outside the flight envelope.

 Computing Plane for alpha= -3.00°
 Calculating aerodynamic coefficients...
 Calculating wing...Main Wing.
 Span pos = -0.80 m, Re = 230034, Cl = -0.00 is outside the flight envelope.
 Span pos = -0.79 m, Re = 230171, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.78 m, Re = 230442, Cl = -0.01 is outside the flight envelope.
 Span pos = -0.77 m, Re = 230848, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.74 m, Re = 231384, Cl = -0.02 is outside the flight envelope.
 Span pos = -0.72 m, Re = 232048, Cl = -0.03 is outside the flight envelope.
 Span pos = -0.69 m, Re = 232834, Cl = -0.03 is outside the flight envelope.
 Span pos = -0.65 m, Re = 233737, Cl = -0.04 is outside the flight envelope.
 Span pos = -0.61 m, Re = 234751, Cl = -0.04 is outside the flight envelope.
 Span pos = -0.57 m, Re = 235870, Cl = -0.05 is outside the flight envelope.
 Span pos = -0.52 m, Re = 237085, Cl = -0.05 is outside the flight envelope.
 Span pos = -0.46 m, Re = 238388, Cl = -0.05 is outside the flight envelope.
 Span pos = -0.41 m, Re = 239771, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.35 m, Re = 241224, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.29 m, Re = 242736, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.23 m, Re = 244298, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.16 m, Re = 245899, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.10 m, Re = 247528, Cl = -0.06 is outside the flight envelope.
 Span pos = -0.03 m, Re = 249174, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.03 m, Re = 249174, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.10 m, Re = 247528, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.16 m, Re = 245899, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.23 m, Re = 244298, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.29 m, Re = 242736, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.35 m, Re = 241224, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.41 m, Re = 239771, Cl = -0.06 is outside the flight envelope.
 Span pos = 0.46 m, Re = 238388, Cl = -0.05 is outside the flight envelope.
 Span pos = 0.52 m, Re = 237085, Cl = -0.05 is outside the flight envelope.
 Span pos = 0.57 m, Re = 235870, Cl = -0.05 is outside the flight envelope.
 Span pos = 0.61 m, Re = 234751, Cl = -0.04 is outside the flight envelope.
 Span pos = 0.65 m, Re = 233737, Cl = -0.04 is outside the flight envelope.
 Span pos = 0.69 m, Re = 232834, Cl = -0.03 is outside the flight envelope.
 Span pos = 0.72 m, Re = 232048, Cl = -0.03 is outside the flight envelope.
 Span pos = 0.74 m, Re = 231384, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.77 m, Re = 230848, Cl = -0.02 is outside the flight envelope.
 Span pos = 0.78 m, Re = 230442, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.79 m, Re = 230171, Cl = -0.01 is outside the flight envelope.
 Span pos = 0.80 m, Re = 230034, Cl = -0.00 is outside the flight envelope.

Panel Analysis completed ... Errors encountered
Nerede hata yapıyorum? Hatanın çözülmesi için hangi dosyaları paylaşmalıyım sizle?
@SideWinder @Jira @Çağlar0707
Genişletmek için tıkla...

Hocam, gördüğün reynolds numberlarında hata alıyorsun, bu sorundan kurtulmak için xfoil Direct analizden bu reynolds numaralarını tanımlayıp analiz etmen gerekiyor sonra wing üzerinde bu değerleri çalışabilirsin.
 

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