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USA 51 AIRFOIL (usa51-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA 51 AIRFOIL (usa51-il)
Reynolds number: 50,000
Max Cl/Cd: 35.22 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa51-il-50000-n5.txt
Download as CSV file: xf-usa51-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 51 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4361   0.10069   0.09385  -0.0273   1.0000   0.0610
  -8.750  -0.4282   0.09691   0.09010  -0.0263   1.0000   0.0579
  -8.500  -0.4296   0.09293   0.08619  -0.0274   1.0000   0.0552
  -8.250  -0.4354   0.08881   0.08218  -0.0294   1.0000   0.0529
  -8.000  -0.4573   0.08281   0.07627  -0.0364   1.0000   0.0487
  -7.750  -0.4551   0.07932   0.07284  -0.0357   1.0000   0.0480
  -7.500  -0.4559   0.07558   0.06912  -0.0359   1.0000   0.0473
  -7.250  -0.4572   0.07170   0.06525  -0.0362   1.0000   0.0467
  -7.000  -0.4579   0.06777   0.06128  -0.0365   1.0000   0.0460
  -6.750  -0.4577   0.06370   0.05714  -0.0365   1.0000   0.0455
  -6.500  -0.4558   0.05970   0.05302  -0.0363   1.0000   0.0450
  -6.250  -0.4524   0.05562   0.04874  -0.0359   1.0000   0.0449
  -6.000  -0.4468   0.05169   0.04455  -0.0352   1.0000   0.0453
  -5.750  -0.4390   0.04787   0.04036  -0.0343   1.0000   0.0463
  -5.500  -0.4286   0.04425   0.03628  -0.0330   1.0000   0.0473
  -5.250  -0.4157   0.04086   0.03238  -0.0316   1.0000   0.0482
  -5.000  -0.4005   0.03776   0.02875  -0.0300   1.0000   0.0487
  -4.750  -0.3842   0.03481   0.02545  -0.0286   1.0000   0.0498
  -4.500  -0.3669   0.03295   0.02346  -0.0274   1.0000   0.0532
  -4.250  -0.3475   0.03109   0.02120  -0.0260   1.0000   0.0577
  -4.000  -0.3258   0.02903   0.01865  -0.0246   1.0000   0.0605
  -3.750  -0.3044   0.02732   0.01673  -0.0234   1.0000   0.0644
  -3.500  -0.2835   0.02623   0.01546  -0.0222   1.0000   0.0727
  -3.250  -0.2610   0.02492   0.01399  -0.0209   1.0000   0.0782
  -3.000  -0.2389   0.02400   0.01291  -0.0197   1.0000   0.0874
  -2.750  -0.2164   0.02323   0.01204  -0.0189   1.0000   0.1012
  -2.500  -0.1950   0.02241   0.01116  -0.0178   1.0000   0.1145
  -2.250  -0.1725   0.02160   0.01042  -0.0171   0.9993   0.1416
  -2.000  -0.1326   0.02022   0.00974  -0.0204   0.9890   0.2771
  -1.750  -0.0621   0.01789   0.00968  -0.0264   0.9906   1.0000
  -1.500  -0.0158   0.01809   0.00938  -0.0305   0.9773   1.0000
  -1.250   0.0278   0.01821   0.00909  -0.0340   0.9628   1.0000
  -1.000   0.0692   0.01829   0.00887  -0.0370   0.9469   1.0000
  -0.750   0.1097   0.01833   0.00863  -0.0397   0.9304   1.0000
  -0.500   0.1500   0.01833   0.00841  -0.0422   0.9131   1.0000
  -0.250   0.1912   0.01827   0.00816  -0.0447   0.8960   1.0000
   0.000   0.2278   0.01819   0.00795  -0.0463   0.8759   1.0000
   0.250   0.2661   0.01809   0.00772  -0.0480   0.8563   1.0000
   0.500   0.3026   0.01800   0.00751  -0.0493   0.8349   1.0000
   0.750   0.3402   0.01791   0.00730  -0.0506   0.8132   1.0000
   1.000   0.3739   0.01789   0.00717  -0.0513   0.7889   1.0000
   1.250   0.4068   0.01791   0.00707  -0.0517   0.7643   1.0000
   1.500   0.4374   0.01799   0.00702  -0.0517   0.7396   1.0000
   1.750   0.4642   0.01817   0.00710  -0.0511   0.7138   1.0000
   2.000   0.4902   0.01838   0.00721  -0.0504   0.6894   1.0000
   2.250   0.5159   0.01863   0.00736  -0.0496   0.6673   1.0000
   2.500   0.5401   0.01893   0.00761  -0.0487   0.6457   1.0000
   2.750   0.5652   0.01924   0.00786  -0.0480   0.6263   1.0000
   3.000   0.5904   0.01955   0.00811  -0.0473   0.6083   1.0000
   3.250   0.6139   0.01988   0.00841  -0.0463   0.5882   1.0000
   3.500   0.6375   0.02020   0.00870  -0.0453   0.5684   1.0000
   3.750   0.6606   0.02052   0.00895  -0.0441   0.5482   1.0000
   4.000   0.6826   0.02085   0.00925  -0.0428   0.5262   1.0000
   4.250   0.7048   0.02119   0.00955  -0.0415   0.5048   1.0000
   4.500   0.7259   0.02156   0.00991  -0.0401   0.4821   1.0000
   4.750   0.7472   0.02196   0.01026  -0.0388   0.4605   1.0000
   5.000   0.7688   0.02239   0.01075  -0.0376   0.4410   1.0000
   5.250   0.7911   0.02284   0.01133  -0.0366   0.4241   1.0000
   5.500   0.8130   0.02331   0.01191  -0.0355   0.4070   1.0000
   5.750   0.8344   0.02380   0.01249  -0.0343   0.3891   1.0000
   6.000   0.8543   0.02430   0.01319  -0.0330   0.3678   1.0000
   6.250   0.8738   0.02481   0.01385  -0.0315   0.3457   1.0000
   6.500   0.8924   0.02538   0.01459  -0.0300   0.3205   1.0000
   6.750   0.9110   0.02601   0.01533  -0.0285   0.2962   1.0000
   7.000   0.9296   0.02672   0.01611  -0.0270   0.2755   1.0000
   7.250   0.9461   0.02743   0.01685  -0.0254   0.2514   1.0000
   7.500   0.9599   0.02815   0.01757  -0.0235   0.2240   1.0000
   7.750   0.9727   0.02903   0.01835  -0.0217   0.1971   1.0000
   8.000   0.9865   0.03000   0.01933  -0.0201   0.1774   1.0000
   8.250   1.0001   0.03105   0.02043  -0.0185   0.1583   1.0000
   8.500   1.0105   0.03234   0.02170  -0.0167   0.1355   1.0000
   8.750   1.0222   0.03360   0.02307  -0.0149   0.1174   1.0000
   9.000   1.0341   0.03489   0.02455  -0.0131   0.0858   1.0000
   9.250   1.0366   0.03678   0.02622  -0.0107   0.0518   1.0000
   9.500   1.0343   0.03898   0.02824  -0.0080   0.0462   1.0000
   9.750   1.0319   0.04128   0.03061  -0.0057   0.0434   1.0000
  10.000   1.0277   0.04385   0.03330  -0.0037   0.0411   1.0000
  10.250   1.0219   0.04673   0.03630  -0.0024   0.0395   1.0000
  10.500   1.0140   0.05008   0.03985  -0.0017   0.0382   1.0000
  10.750   1.0084   0.05347   0.04339  -0.0016   0.0370   1.0000
  11.000   1.0036   0.05703   0.04716  -0.0018   0.0359   1.0000
  11.250   0.9995   0.06067   0.05098  -0.0023   0.0350   1.0000
  11.500   0.9955   0.06446   0.05496  -0.0029   0.0343   1.0000
  11.750   0.9924   0.06825   0.05892  -0.0036   0.0338   1.0000
  12.000   0.9903   0.07199   0.06283  -0.0043   0.0333   1.0000
  12.250   0.9886   0.07576   0.06676  -0.0049   0.0328   1.0000
  12.500   0.9869   0.07960   0.07076  -0.0056   0.0322   1.0000
  12.750   0.9850   0.08355   0.07485  -0.0065   0.0315   1.0000
  13.000   0.9835   0.08754   0.07898  -0.0073   0.0310   1.0000
  13.250   0.9815   0.09166   0.08321  -0.0081   0.0303   1.0000
  13.500   0.9799   0.09583   0.08744  -0.0086   0.0295   1.0000
  13.750   0.9737   0.10114   0.09299  -0.0110   0.0293   1.0000
  14.000   0.9672   0.10664   0.09870  -0.0135   0.0292   1.0000
  14.250   0.9589   0.11271   0.10498  -0.0165   0.0291   1.0000
  14.500   0.9497   0.11921   0.11166  -0.0199   0.0291   1.0000
  14.750   0.9393   0.12631   0.11894  -0.0238   0.0291   1.0000
  15.000   0.9312   0.13311   0.12587  -0.0274   0.0293   1.0000
  15.250   0.9209   0.14096   0.13390  -0.0318   0.0296   1.0000
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