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USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 40 AIRFOIL (usa40-il)
Reynolds number: 50,000
Max Cl/Cd: 35.33 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa40-il-50000-n5.txt
Download as CSV file: xf-usa40-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 40 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2990   0.09980   0.09244  -0.0395   1.0000   0.0862
  -8.500  -0.3045   0.09678   0.08953  -0.0396   1.0000   0.0850
  -8.250  -0.3132   0.09387   0.08673  -0.0394   1.0000   0.0841
  -7.750  -0.3769   0.08523   0.07840  -0.0414   1.0000   0.0797
  -7.500  -0.3873   0.08212   0.07539  -0.0415   1.0000   0.0795
  -7.250  -0.3975   0.07860   0.07193  -0.0424   1.0000   0.0793
  -7.000  -0.4068   0.07472   0.06808  -0.0438   1.0000   0.0790
  -6.750  -0.4143   0.07065   0.06400  -0.0454   1.0000   0.0787
  -6.500  -0.3938   0.06356   0.05666  -0.0548   0.9918   0.0782
  -6.250  -0.3658   0.05636   0.04904  -0.0648   0.9826   0.0779
  -6.000  -0.3351   0.05013   0.04225  -0.0729   0.9732   0.0779
  -5.750  -0.3004   0.04509   0.03655  -0.0795   0.9645   0.0789
  -5.500  -0.2619   0.04181   0.03285  -0.0846   0.9571   0.0810
  -5.250  -0.2286   0.03991   0.03082  -0.0872   0.9471   0.0834
  -5.000  -0.1885   0.03747   0.02799  -0.0911   0.9392   0.0856
  -4.750  -0.1509   0.03525   0.02535  -0.0940   0.9291   0.0878
  -4.500  -0.1114   0.03332   0.02292  -0.0967   0.9194   0.0909
  -4.250  -0.0715   0.03195   0.02154  -0.0994   0.9100   0.0955
  -4.000  -0.0358   0.03078   0.02020  -0.1009   0.8987   0.1008
  -3.750   0.0072   0.02941   0.01865  -0.1035   0.8907   0.1065
  -3.500   0.0387   0.02858   0.01782  -0.1041   0.8781   0.1144
  -3.250   0.0760   0.02762   0.01685  -0.1055   0.8684   0.1251
  -3.000   0.1088   0.02686   0.01611  -0.1062   0.8564   0.1392
  -2.750   0.1406   0.02621   0.01551  -0.1068   0.8437   0.1594
  -2.500   0.1793   0.02536   0.01472  -0.1084   0.8343   0.1938
  -2.250   0.2085   0.02466   0.01419  -0.1086   0.8200   0.2396
  -2.000   0.2392   0.02394   0.01378  -0.1091   0.8066   0.3013
  -1.750   0.2720   0.02330   0.01340  -0.1095   0.7949   0.3774
  -1.500   0.3004   0.02282   0.01322  -0.1090   0.7813   0.4568
  -1.250   0.3230   0.02254   0.01336  -0.1069   0.7667   0.5555
  -1.000   0.3438   0.02243   0.01348  -0.1040   0.7528   0.6488
  -0.750   0.3671   0.02230   0.01333  -0.1016   0.7398   0.7160
  -0.500   0.3899   0.02214   0.01309  -0.0994   0.7259   0.7650
  -0.250   0.4106   0.02198   0.01287  -0.0971   0.7108   0.8076
   0.000   0.4318   0.02173   0.01257  -0.0947   0.6963   0.8510
   0.250   0.4592   0.02140   0.01217  -0.0936   0.6821   0.9035
   0.500   0.4980   0.02120   0.01177  -0.0952   0.6668   1.0000
   0.750   0.5298   0.02132   0.01164  -0.0959   0.6521   1.0000
   1.000   0.5592   0.02156   0.01166  -0.0963   0.6365   1.0000
   1.250   0.5884   0.02182   0.01171  -0.0966   0.6212   1.0000
   1.500   0.6178   0.02208   0.01178  -0.0969   0.6069   1.0000
   1.750   0.6479   0.02233   0.01180  -0.0971   0.5938   1.0000
   2.000   0.6757   0.02267   0.01200  -0.0972   0.5795   1.0000
   2.250   0.7028   0.02306   0.01227  -0.0971   0.5655   1.0000
   2.500   0.7308   0.02342   0.01248  -0.0971   0.5532   1.0000
   2.750   0.7592   0.02376   0.01268  -0.0971   0.5415   1.0000
   3.000   0.7850   0.02423   0.01308  -0.0969   0.5288   1.0000
   3.250   0.8125   0.02464   0.01337  -0.0968   0.5181   1.0000
   3.500   0.8393   0.02508   0.01373  -0.0967   0.5074   1.0000
   3.750   0.8652   0.02560   0.01420  -0.0965   0.4969   1.0000
   4.000   0.8930   0.02600   0.01448  -0.0964   0.4879   1.0000
   4.250   0.9175   0.02664   0.01513  -0.0960   0.4778   1.0000
   4.500   0.9455   0.02706   0.01544  -0.0959   0.4698   1.0000
   4.750   0.9690   0.02777   0.01621  -0.0955   0.4603   1.0000
   5.000   0.9963   0.02826   0.01661  -0.0954   0.4527   1.0000
   5.250   1.0196   0.02903   0.01743  -0.0949   0.4443   1.0000
   5.500   1.0453   0.02963   0.01803  -0.0946   0.4367   1.0000
   5.750   1.0701   0.03034   0.01874  -0.0943   0.4296   1.0000
   6.000   1.0926   0.03116   0.01964  -0.0938   0.4219   1.0000
   6.250   1.1203   0.03171   0.02013  -0.0937   0.4160   1.0000
   6.500   1.1395   0.03277   0.02137  -0.0929   0.4084   1.0000
   6.750   1.1628   0.03357   0.02221  -0.0924   0.4017   1.0000
   7.000   1.1882   0.03422   0.02284  -0.0920   0.3955   1.0000
   7.250   1.2043   0.03533   0.02415  -0.0908   0.3869   1.0000
   7.500   1.2318   0.03559   0.02430  -0.0904   0.3794   1.0000
   7.750   1.2433   0.03683   0.02576  -0.0887   0.3699   1.0000
   8.000   1.2696   0.03697   0.02580  -0.0881   0.3614   1.0000
   8.250   1.2785   0.03827   0.02734  -0.0862   0.3520   1.0000
   8.500   1.3030   0.03846   0.02745  -0.0854   0.3439   1.0000
   8.750   1.3098   0.03987   0.02911  -0.0833   0.3352   1.0000
   9.000   1.3300   0.04029   0.02953  -0.0822   0.3275   1.0000
   9.250   1.3370   0.04166   0.03109  -0.0801   0.3197   1.0000
   9.500   1.3502   0.04245   0.03195  -0.0785   0.3119   1.0000
   9.750   1.3585   0.04358   0.03319  -0.0765   0.3045   1.0000
  10.000   1.3599   0.04500   0.03476  -0.0739   0.2971   1.0000
  10.250   1.3725   0.04569   0.03547  -0.0722   0.2901   1.0000
  10.500   1.3623   0.04823   0.03826  -0.0696   0.2831   1.0000
  10.750   1.3719   0.04922   0.03930  -0.0680   0.2766   1.0000
  11.000   1.3617   0.05216   0.04244  -0.0662   0.2702   1.0000
  11.250   1.3528   0.05518   0.04562  -0.0649   0.2636   1.0000
  11.500   1.3604   0.05656   0.04703  -0.0638   0.2576   1.0000
  11.750   1.3277   0.06301   0.05379  -0.0638   0.2514   1.0000
  12.000   1.3240   0.06611   0.05699  -0.0636   0.2453   1.0000
  12.250   1.3022   0.07204   0.06309  -0.0645   0.2394   1.0000
  12.500   1.2529   0.08286   0.07413  -0.0678   0.2321   1.0000
  12.750   1.2870   0.08023   0.07152  -0.0656   0.2271   1.0000
  13.000   1.1968   0.09923   0.09071  -0.0730   0.2165   1.0000
  13.250   1.2278   0.09669   0.08823  -0.0708   0.2124   1.0000
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