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GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 401 AIRFOIL (goe401-il)
Reynolds number: 50,000
Max Cl/Cd: 38.56 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe401-il-50000-n5.txt
Download as CSV file: xf-goe401-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3311   0.10857   0.10164  -0.0240   1.0000   0.0925
  -8.000  -0.3380   0.10780   0.10101  -0.0255   1.0000   0.0929
  -7.750  -0.3401   0.10678   0.10007  -0.0288   1.0000   0.0932
  -7.500  -0.3219   0.09909   0.09239  -0.0237   1.0000   0.0951
  -7.250  -0.3146   0.09563   0.08897  -0.0226   1.0000   0.0973
  -7.000  -0.3104   0.09297   0.08639  -0.0224   1.0000   0.1002
  -6.750  -0.3084   0.09077   0.08427  -0.0231   1.0000   0.1037
  -6.500  -0.3085   0.08963   0.08322  -0.0264   1.0000   0.1072
  -6.250  -0.3056   0.08924   0.08283  -0.0318   1.0000   0.1083
  -6.000  -0.3009   0.08414   0.07788  -0.0277   1.0000   0.1099
  -5.750  -0.2966   0.08103   0.07485  -0.0255   1.0000   0.1120
  -5.500  -0.2931   0.07859   0.07247  -0.0247   1.0000   0.1144
  -5.250  -0.2898   0.07643   0.07034  -0.0246   1.0000   0.1174
  -5.000  -0.2833   0.07500   0.06887  -0.0270   1.0000   0.1218
  -4.750  -0.2720   0.07377   0.06752  -0.0308   1.0000   0.1235
  -4.500  -0.2707   0.07017   0.06403  -0.0278   1.0000   0.1248
  -4.250  -0.2505   0.06654   0.06042  -0.0290   0.9943   0.1294
  -4.000  -0.2037   0.06287   0.05652  -0.0382   0.9811   0.1401
  -3.750  -0.1693   0.05915   0.05271  -0.0422   0.9688   0.1473
  -3.250  -0.0951   0.05264   0.04587  -0.0521   0.9452   0.1603
  -3.000  -0.0280   0.04787   0.04019  -0.0616   0.9357   0.0925
  -2.750   0.0038   0.04471   0.03696  -0.0640   0.9239   0.0900
  -2.500   0.0413   0.04200   0.03400  -0.0670   0.9125   0.0883
  -2.250   0.0836   0.03914   0.03080  -0.0706   0.9028   0.0840
  -2.000   0.1299   0.03657   0.02750  -0.0737   0.8921   0.0780
  -1.750   0.1648   0.03441   0.02511  -0.0754   0.8795   0.0771
  -1.500   0.2008   0.03249   0.02291  -0.0770   0.8667   0.0764
  -1.250   0.2373   0.03073   0.02082  -0.0783   0.8537   0.0762
  -1.000   0.2739   0.02927   0.01891  -0.0793   0.8399   0.0780
  -0.750   0.3065   0.02797   0.01751  -0.0800   0.8247   0.0807
  -0.500   0.3396   0.02683   0.01613  -0.0804   0.8088   0.0820
  -0.250   0.3717   0.02578   0.01482  -0.0806   0.7917   0.0832
   0.000   0.4027   0.02488   0.01367  -0.0803   0.7742   0.0850
   0.250   0.4371   0.02407   0.01256  -0.0806   0.7562   0.0879
   0.500   0.4698   0.02337   0.01155  -0.0805   0.7378   0.0925
   0.750   0.4993   0.02291   0.01105  -0.0802   0.7193   0.1008
   1.000   0.5273   0.02249   0.01049  -0.0795   0.7008   0.1114
   1.250   0.5534   0.02215   0.01006  -0.0786   0.6813   0.1255
   1.500   0.5798   0.02180   0.00970  -0.0779   0.6629   0.1583
   1.750   0.6060   0.02113   0.00939  -0.0777   0.6453   0.2624
   2.000   0.6483   0.01972   0.00908  -0.0800   0.6273   1.0000
   2.250   0.6738   0.02001   0.00907  -0.0792   0.6110   1.0000
   2.500   0.6991   0.02032   0.00914  -0.0783   0.5955   1.0000
   2.750   0.7242   0.02066   0.00928  -0.0775   0.5806   1.0000
   3.000   0.7491   0.02102   0.00949  -0.0768   0.5665   1.0000
   3.250   0.7741   0.02139   0.00973  -0.0760   0.5531   1.0000
   3.500   0.7990   0.02179   0.01000  -0.0753   0.5406   1.0000
   3.750   0.8242   0.02218   0.01029  -0.0746   0.5289   1.0000
   4.000   0.8489   0.02261   0.01064  -0.0739   0.5173   1.0000
   4.250   0.8728   0.02310   0.01110  -0.0731   0.5056   1.0000
   4.500   0.8973   0.02359   0.01157  -0.0724   0.4950   1.0000
   4.750   0.9225   0.02405   0.01196  -0.0718   0.4852   1.0000
   5.000   0.9454   0.02464   0.01261  -0.0710   0.4743   1.0000
   5.250   0.9695   0.02521   0.01319  -0.0703   0.4647   1.0000
   5.500   0.9938   0.02577   0.01377  -0.0695   0.4553   1.0000
   5.750   1.0162   0.02646   0.01457  -0.0687   0.4455   1.0000
   6.000   1.0412   0.02705   0.01514  -0.0681   0.4373   1.0000
   6.250   1.0624   0.02782   0.01611  -0.0672   0.4274   1.0000
   6.500   1.0858   0.02853   0.01689  -0.0664   0.4193   1.0000
   6.750   1.1075   0.02932   0.01784  -0.0655   0.4104   1.0000
   7.000   1.1295   0.03014   0.01880  -0.0647   0.4024   1.0000
   7.250   1.1511   0.03098   0.01983  -0.0638   0.3941   1.0000
   7.500   1.1718   0.03191   0.02094  -0.0628   0.3864   1.0000
   7.750   1.1926   0.03274   0.02195  -0.0618   0.3779   1.0000
   8.000   1.2105   0.03365   0.02309  -0.0605   0.3685   1.0000
   8.250   1.2341   0.03408   0.02362  -0.0595   0.3594   1.0000
   8.500   1.2478   0.03494   0.02476  -0.0576   0.3474   1.0000
   8.750   1.2630   0.03559   0.02564  -0.0558   0.3354   1.0000
   9.000   1.2788   0.03608   0.02632  -0.0540   0.3234   1.0000
   9.250   1.2947   0.03646   0.02691  -0.0521   0.3112   1.0000
   9.500   1.3068   0.03684   0.02748  -0.0497   0.2970   1.0000
   9.750   1.3146   0.03737   0.02823  -0.0470   0.2811   1.0000
  10.000   1.3204   0.03808   0.02916  -0.0442   0.2649   1.0000
  10.250   1.3223   0.03896   0.03022  -0.0411   0.2465   1.0000
  10.500   1.3179   0.03988   0.03114  -0.0373   0.2249   1.0000
  10.750   1.3076   0.04167   0.03299  -0.0339   0.2002   1.0000
  11.000   1.2963   0.04403   0.03533  -0.0313   0.1742   1.0000
  11.250   1.2832   0.04713   0.03833  -0.0297   0.1487   1.0000
  11.500   1.2685   0.05092   0.04205  -0.0290   0.1284   1.0000
  11.750   1.2535   0.05525   0.04629  -0.0290   0.1144   1.0000
  12.000   1.2386   0.05997   0.05096  -0.0295   0.1039   1.0000
  12.250   1.2245   0.06487   0.05583  -0.0304   0.0963   1.0000
  12.500   1.2113   0.06987   0.06082  -0.0315   0.0903   1.0000
  12.750   1.1994   0.07484   0.06576  -0.0326   0.0846   1.0000
  13.000   1.1892   0.07964   0.07058  -0.0337   0.0793   1.0000
  13.250   1.1800   0.08427   0.07513  -0.0346   0.0748   1.0000
  13.500   1.1740   0.08863   0.07960  -0.0354   0.0699   1.0000
  13.750   1.1692   0.09269   0.08364  -0.0361   0.0659   1.0000
  14.000   1.1679   0.09625   0.08723  -0.0362   0.0625   1.0000
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