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GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 401 AIRFOIL (goe401-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.71 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe401-il-1000000.txt
Download as CSV file: xf-goe401-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 401 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3298   0.09042   0.08884  -0.0191   1.0000   0.0176
  -7.750  -0.3375   0.08787   0.08633  -0.0197   1.0000   0.0180
  -7.500  -0.3472   0.08526   0.08376  -0.0202   1.0000   0.0181
  -7.250  -0.3231   0.08002   0.07850  -0.0289   0.9977   0.0182
  -7.000  -0.2998   0.07368   0.07213  -0.0367   0.9938   0.0184
  -6.750  -0.2773   0.07064   0.06908  -0.0395   0.9887   0.0186
  -6.500  -0.2540   0.06768   0.06611  -0.0432   0.9794   0.0189
  -6.250  -0.2315   0.06448   0.06289  -0.0474   0.9605   0.0192
  -6.000  -0.1905   0.06032   0.05867  -0.0561   0.9448   0.0203
  -5.250  -0.0587   0.02741   0.02510  -0.0781   0.8183   0.0227
  -5.000  -0.0415   0.02548   0.02308  -0.0783   0.8029   0.0230
  -4.750  -0.0230   0.02370   0.02122  -0.0787   0.7883   0.0234
  -4.500  -0.0031   0.02168   0.01909  -0.0793   0.7743   0.0240
  -4.250   0.0184   0.01942   0.01670  -0.0803   0.7610   0.0249
  -4.000   0.0482   0.01659   0.01363  -0.0819   0.7501   0.0270
  -3.750   0.0715   0.01416   0.01101  -0.0825   0.7389   0.0271
  -3.500   0.1012   0.02375   0.02010  -0.0895   0.7524   0.0278
  -3.250   0.1235   0.02295   0.01920  -0.0890   0.7378   0.0282
  -3.000   0.1465   0.02190   0.01802  -0.0884   0.7239   0.0287
  -2.750   0.1700   0.02078   0.01676  -0.0879   0.7100   0.0294
  -2.500   0.1939   0.01926   0.01505  -0.0871   0.6956   0.0309
  -2.250   0.2162   0.01543   0.01059  -0.0854   0.6829   0.0340
  -2.000   0.2395   0.01432   0.00936  -0.0847   0.6665   0.0349
  -1.750   0.2642   0.01377   0.00870  -0.0841   0.6485   0.0356
  -1.500   0.2889   0.01322   0.00800  -0.0833   0.6271   0.0366
  -1.250   0.3135   0.01268   0.00726  -0.0825   0.6026   0.0381
  -1.000   0.3375   0.01055   0.00460  -0.0809   0.5767   0.0313
  -0.750   0.3619   0.00997   0.00378  -0.0799   0.5445   0.0308
  -0.250   0.4112   0.00952   0.00297  -0.0783   0.4841   0.0313
   0.000   0.4363   0.00935   0.00268  -0.0776   0.4649   0.0315
   0.500   0.4874   0.00904   0.00224  -0.0763   0.4404   0.0318
   0.750   0.5131   0.00894   0.00208  -0.0757   0.4311   0.0321
   1.000   0.5390   0.00887   0.00198  -0.0752   0.4230   0.0327
   1.250   0.5649   0.00881   0.00188  -0.0746   0.4159   0.0330
   1.500   0.5910   0.00873   0.00179  -0.0741   0.4092   0.0335
   1.750   0.6164   0.00865   0.00165  -0.0734   0.4026   0.0350
   2.000   0.6429   0.00860   0.00160  -0.0730   0.3974   0.0366
   2.250   0.6690   0.00861   0.00159  -0.0725   0.3912   0.0383
   2.500   0.6953   0.00864   0.00161  -0.0721   0.3856   0.0403
   2.750   0.7216   0.00860   0.00165  -0.0717   0.3805   0.0653
   3.000   0.7471   0.00857   0.00177  -0.0711   0.3747   0.1425
   3.250   0.7733   0.00858   0.00185  -0.0707   0.3681   0.1777
   3.500   0.7970   0.00831   0.00198  -0.0700   0.3604   0.4075
   3.750   0.8751   0.00726   0.00221  -0.0819   0.3516   1.0000
   4.000   0.9003   0.00738   0.00229  -0.0812   0.3450   1.0000
   4.250   0.9255   0.00750   0.00238  -0.0806   0.3363   1.0000
   4.500   0.9503   0.00765   0.00247  -0.0799   0.3274   1.0000
   4.750   0.9756   0.00776   0.00258  -0.0793   0.3203   1.0000
   5.000   1.0002   0.00792   0.00270  -0.0786   0.3119   1.0000
   5.250   1.0254   0.00804   0.00282  -0.0780   0.3042   1.0000
   5.500   1.0498   0.00822   0.00295  -0.0773   0.2943   1.0000
   5.750   1.0738   0.00843   0.00311  -0.0765   0.2815   1.0000
   6.000   1.0975   0.00866   0.00328  -0.0757   0.2666   1.0000
   6.250   1.1210   0.00891   0.00347  -0.0749   0.2512   1.0000
   6.750   1.1673   0.00946   0.00391  -0.0731   0.2224   1.0000
   7.000   1.1898   0.00979   0.00416  -0.0722   0.2038   1.0000
   7.250   1.2117   0.01017   0.00445  -0.0711   0.1850   1.0000
   7.500   1.2324   0.01065   0.00480  -0.0699   0.1598   1.0000
   7.750   1.2473   0.01163   0.00544  -0.0678   0.1056   1.0000
   8.000   1.2608   0.01272   0.00625  -0.0655   0.0606   1.0000
   8.250   1.2817   0.01315   0.00668  -0.0644   0.0530   1.0000
   8.500   1.3027   0.01357   0.00709  -0.0632   0.0475   1.0000
   8.750   1.3237   0.01397   0.00750  -0.0621   0.0409   1.0000
   9.000   1.3420   0.01459   0.00801  -0.0606   0.0282   1.0000
   9.250   1.3601   0.01520   0.00857  -0.0590   0.0206   1.0000
   9.500   1.3777   0.01584   0.00920  -0.0574   0.0173   1.0000
   9.750   1.3970   0.01630   0.00972  -0.0560   0.0164   1.0000
  10.000   1.4148   0.01686   0.01033  -0.0544   0.0153   1.0000
  10.250   1.4306   0.01754   0.01105  -0.0526   0.0142   1.0000
  10.500   1.4443   0.01832   0.01190  -0.0504   0.0134   1.0000
  10.750   1.4605   0.01887   0.01251  -0.0486   0.0130   1.0000
  11.000   1.4748   0.01949   0.01320  -0.0466   0.0125   1.0000
  11.250   1.4857   0.02012   0.01389  -0.0440   0.0121   1.0000
  11.500   1.4946   0.02084   0.01466  -0.0411   0.0115   1.0000
  11.750   1.5016   0.02172   0.01560  -0.0382   0.0112   1.0000
  12.000   1.5017   0.02306   0.01704  -0.0346   0.0106   1.0000
  12.250   1.5011   0.02456   0.01866  -0.0315   0.0104   1.0000
  12.500   1.5083   0.02569   0.01987  -0.0295   0.0102   1.0000
  12.750   1.5155   0.02692   0.02118  -0.0279   0.0100   1.0000
  13.000   1.5195   0.02850   0.02285  -0.0263   0.0098   1.0000
  13.250   1.5226   0.03031   0.02476  -0.0250   0.0097   1.0000
  13.500   1.5248   0.03236   0.02690  -0.0240   0.0095   1.0000
  13.750   1.5273   0.03452   0.02915  -0.0234   0.0092   1.0000
  14.000   1.5243   0.03740   0.03214  -0.0230   0.0092   1.0000
  14.250   1.5217   0.04042   0.03526  -0.0229   0.0090   1.0000
  14.500   1.5205   0.04340   0.03833  -0.0230   0.0088   1.0000
  14.750   1.5145   0.04710   0.04214  -0.0235   0.0087   1.0000
  15.000   1.5089   0.05086   0.04600  -0.0241   0.0086   1.0000
  15.250   1.5016   0.05499   0.05023  -0.0250   0.0085   1.0000
  15.500   1.4939   0.05926   0.05459  -0.0260   0.0083   1.0000
  15.750   1.4838   0.06394   0.05938  -0.0272   0.0083   1.0000
  16.000   1.4685   0.06943   0.06498  -0.0287   0.0082   1.0000
  16.250   1.4590   0.07414   0.06978  -0.0300   0.0081   1.0000
  16.500   1.4454   0.07945   0.07519  -0.0315   0.0080   1.0000
  16.750   1.4253   0.08549   0.08133  -0.0329   0.0078   1.0000
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