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GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 392 AIRFOIL (goe392-il)
Reynolds number: 200,000
Max Cl/Cd: 78.8 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe392-il-200000.txt
Download as CSV file: xf-goe392-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 392 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3147   0.09937   0.09629  -0.0360   1.0000   0.0277
  -8.000  -0.3242   0.09774   0.09474  -0.0344   1.0000   0.0282
  -7.750  -0.3390   0.09674   0.09383  -0.0315   1.0000   0.0284
  -7.500  -0.3321   0.09373   0.09086  -0.0363   0.9962   0.0292
  -7.250  -0.3121   0.08937   0.08651  -0.0461   0.9876   0.0298
  -7.000  -0.2815   0.08351   0.08062  -0.0583   0.9795   0.0302
  -6.750  -0.2506   0.07718   0.07423  -0.0699   0.9722   0.0303
  -6.500  -0.2234   0.07092   0.06785  -0.0796   0.9636   0.0304
  -6.250  -0.2100   0.06280   0.05976  -0.0849   0.9587   0.0317
  -6.000  -0.1930   0.05939   0.05630  -0.0865   0.9511   0.0330
  -5.750  -0.1637   0.05464   0.05146  -0.0927   0.9460   0.0347
  -5.500  -0.1367   0.04960   0.04626  -0.0986   0.9376   0.0368
  -5.250  -0.0999   0.04380   0.04013  -0.1061   0.9327   0.0403
  -5.000  -0.0669   0.03938   0.03491  -0.1111   0.9239   0.0444
  -4.750  -0.0386   0.03474   0.03042  -0.1142   0.9204   0.0486
  -4.500   0.0005   0.03102   0.02615  -0.1186   0.9177   0.0597
  -4.250   0.0249   0.02881   0.02374  -0.1194   0.9086   0.0733
  -4.000   0.0589   0.02709   0.02199  -0.1224   0.9050   0.1071
  -3.500   0.1340   0.02028   0.01369  -0.1225   0.8922   0.0533
  -3.250   0.1667   0.01826   0.01122  -0.1220   0.8840   0.0410
  -3.000   0.2037   0.01645   0.00913  -0.1232   0.8784   0.0403
  -2.750   0.2336   0.01561   0.00808  -0.1232   0.8688   0.0442
  -2.500   0.2644   0.01411   0.00650  -0.1235   0.8609   0.0458
  -2.250   0.2939   0.01318   0.00553  -0.1237   0.8519   0.0511
  -2.000   0.3210   0.01263   0.00487  -0.1235   0.8414   0.0615
  -1.750   0.3496   0.01218   0.00434  -0.1234   0.8316   0.0827
  -1.500   0.3732   0.01100   0.00428  -0.1230   0.8220   0.4375
  -1.250   0.3968   0.01062   0.00414  -0.1221   0.8112   0.5269
  -1.000   0.4152   0.01005   0.00418  -0.1198   0.7998   0.7190
  -0.750   0.4829   0.00952   0.00389  -0.1278   0.7894   1.0000
  -0.500   0.5087   0.00961   0.00379  -0.1273   0.7781   1.0000
  -0.250   0.5351   0.00972   0.00369  -0.1270   0.7675   1.0000
   0.000   0.5598   0.00982   0.00365  -0.1263   0.7564   1.0000
   0.250   0.5843   0.00994   0.00365  -0.1257   0.7453   1.0000
   0.500   0.6094   0.01006   0.00365  -0.1251   0.7347   1.0000
   0.750   0.6352   0.01017   0.00366  -0.1247   0.7249   1.0000
   1.000   0.6607   0.01029   0.00368  -0.1242   0.7147   1.0000
   1.250   0.6851   0.01042   0.00374  -0.1236   0.7039   1.0000
   1.500   0.7102   0.01055   0.00381  -0.1230   0.6938   1.0000
   1.750   0.7359   0.01069   0.00387  -0.1226   0.6841   1.0000
   2.000   0.7611   0.01082   0.00398  -0.1221   0.6741   1.0000
   2.250   0.7856   0.01097   0.00411  -0.1215   0.6636   1.0000
   2.500   0.8108   0.01113   0.00425  -0.1210   0.6540   1.0000
   2.750   0.8368   0.01129   0.00437  -0.1207   0.6449   1.0000
   3.000   0.8608   0.01142   0.00449  -0.1199   0.6327   1.0000
   3.250   0.8793   0.01140   0.00438  -0.1177   0.6048   1.0000
   3.500   0.8974   0.01147   0.00437  -0.1155   0.5746   1.0000
   3.750   0.9180   0.01165   0.00448  -0.1140   0.5513   1.0000
   4.000   0.9333   0.01191   0.00457  -0.1113   0.5077   1.0000
   4.250   0.9429   0.01247   0.00473  -0.1076   0.4291   1.0000
   4.500   0.9466   0.01366   0.00521  -0.1032   0.3172   1.0000
   4.750   0.9346   0.01637   0.00664  -0.0969   0.0803   1.0000
   5.000   0.9490   0.01729   0.00745  -0.0945   0.0358   1.0000
   5.250   0.9681   0.01784   0.00817  -0.0928   0.0333   1.0000
   5.500   0.9839   0.01858   0.00909  -0.0906   0.0296   1.0000
   5.750   0.9956   0.01951   0.01021  -0.0877   0.0273   1.0000
   6.000   1.0033   0.02047   0.01134  -0.0842   0.0268   1.0000
   6.250   1.0063   0.02166   0.01265  -0.0800   0.0266   1.0000
   6.500   1.0109   0.02284   0.01391  -0.0762   0.0267   1.0000
   6.750   1.0176   0.02400   0.01514  -0.0729   0.0271   1.0000
   7.000   1.0262   0.02517   0.01643  -0.0699   0.0279   1.0000
   7.250   1.0370   0.02640   0.01776  -0.0672   0.0296   1.0000
   7.500   1.0498   0.02793   0.01932  -0.0649   0.0301   1.0000
   7.750   1.0706   0.02957   0.02098  -0.0636   0.0297   1.0000
  12.000   1.2419   0.08871   0.08369  -0.0391   0.0253   1.0000
  12.250   1.2205   0.09155   0.08671  -0.0369   0.0252   1.0000
  12.500   1.2021   0.09524   0.09056  -0.0358   0.0253   1.0000
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