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E226 (10.19%) (e226-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E226 (10.19%) (e226-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.82 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e226-il-1000000.txt
Download as CSV file: xf-e226-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E226  (10.19%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.5942   0.13873   0.13700   0.0061   1.0000   0.0114
 -13.000  -0.5925   0.13404   0.13232   0.0041   1.0000   0.0115
  -9.500  -0.8506   0.02772   0.02381  -0.0346   1.0000   0.0101
  -9.250  -0.8348   0.02649   0.02241  -0.0332   1.0000   0.0099
  -9.000  -0.8183   0.02530   0.02108  -0.0318   1.0000   0.0098
  -8.750  -0.8030   0.02334   0.01902  -0.0302   1.0000   0.0095
  -8.500  -0.7900   0.02133   0.01681  -0.0282   1.0000   0.0095
  -8.250  -0.7752   0.01978   0.01510  -0.0262   1.0000   0.0094
  -8.000  -0.7597   0.01861   0.01381  -0.0242   1.0000   0.0094
  -7.750  -0.7436   0.01786   0.01294  -0.0222   1.0000   0.0096
  -7.500  -0.7205   0.01710   0.01208  -0.0216   0.9992   0.0097
  -7.250  -0.6895   0.01564   0.01049  -0.0228   0.9970   0.0098
  -7.000  -0.6587   0.01408   0.00883  -0.0240   0.9946   0.0099
  -6.750  -0.6298   0.01271   0.00738  -0.0248   0.9910   0.0104
  -6.500  -0.5974   0.01194   0.00656  -0.0261   0.9880   0.0108
  -6.250  -0.5634   0.01134   0.00591  -0.0277   0.9858   0.0111
  -6.000  -0.5299   0.01080   0.00532  -0.0290   0.9830   0.0116
  -5.750  -0.4994   0.01034   0.00481  -0.0297   0.9772   0.0120
  -5.500  -0.4668   0.00991   0.00433  -0.0308   0.9725   0.0124
  -5.250  -0.4385   0.00956   0.00393  -0.0309   0.9642   0.0128
  -5.000  -0.4093   0.00924   0.00357  -0.0311   0.9565   0.0133
  -4.750  -0.3837   0.00887   0.00313  -0.0305   0.9457   0.0149
  -4.500  -0.3579   0.00860   0.00282  -0.0300   0.9349   0.0169
  -4.250  -0.3331   0.00820   0.00249  -0.0293   0.9240   0.0362
  -4.000  -0.3097   0.00762   0.00215  -0.0285   0.9126   0.0972
  -3.750  -0.2849   0.00723   0.00194  -0.0280   0.9009   0.1458
  -3.500  -0.2594   0.00693   0.00177  -0.0275   0.8893   0.1870
  -3.250  -0.2339   0.00664   0.00162  -0.0271   0.8777   0.2339
  -3.000  -0.2082   0.00638   0.00148  -0.0267   0.8660   0.2804
  -2.750  -0.1822   0.00616   0.00137  -0.0263   0.8537   0.3234
  -2.500  -0.1558   0.00597   0.00127  -0.0260   0.8411   0.3635
  -2.250  -0.1299   0.00573   0.00118  -0.0256   0.8280   0.4218
  -2.000  -0.1036   0.00554   0.00111  -0.0253   0.8148   0.4691
  -1.750  -0.0768   0.00543   0.00105  -0.0250   0.8015   0.5016
  -1.500  -0.0500   0.00533   0.00100  -0.0247   0.7877   0.5343
  -1.250  -0.0231   0.00525   0.00095  -0.0245   0.7736   0.5674
  -1.000   0.0037   0.00516   0.00092  -0.0242   0.7591   0.6001
  -0.750   0.0305   0.00509   0.00090  -0.0239   0.7442   0.6321
  -0.500   0.0573   0.00503   0.00088  -0.0236   0.7288   0.6634
  -0.250   0.0840   0.00499   0.00088  -0.0233   0.7129   0.6934
   0.000   0.1108   0.00495   0.00088  -0.0229   0.6966   0.7224
   0.250   0.1374   0.00493   0.00089  -0.0225   0.6796   0.7510
   0.500   0.1640   0.00493   0.00091  -0.0222   0.6618   0.7784
   0.750   0.1904   0.00493   0.00093  -0.0217   0.6439   0.8045
   1.000   0.2168   0.00494   0.00097  -0.0213   0.6255   0.8293
   1.250   0.2430   0.00497   0.00101  -0.0208   0.6058   0.8535
   1.500   0.2689   0.00502   0.00106  -0.0202   0.5862   0.8764
   1.750   0.2949   0.00507   0.00111  -0.0197   0.5655   0.8987
   2.000   0.3207   0.00515   0.00118  -0.0190   0.5443   0.9196
   2.250   0.3473   0.00525   0.00125  -0.0186   0.5220   0.9390
   2.500   0.3758   0.00539   0.00133  -0.0186   0.4982   0.9555
   2.750   0.4075   0.00555   0.00142  -0.0194   0.4716   0.9675
   3.000   0.4409   0.00572   0.00151  -0.0207   0.4458   0.9763
   3.250   0.4734   0.00592   0.00161  -0.0217   0.4193   0.9844
   3.500   0.5106   0.00614   0.00173  -0.0239   0.3877   0.9877
   3.750   0.5456   0.00646   0.00186  -0.0256   0.3426   0.9921
   4.000   0.5802   0.00680   0.00201  -0.0273   0.2969   0.9958
   4.250   0.6160   0.00711   0.00218  -0.0293   0.2607   0.9990
   4.500   0.6433   0.00741   0.00235  -0.0294   0.2277   1.0000
   4.750   0.6641   0.00779   0.00255  -0.0282   0.1902   1.0000
   5.000   0.6855   0.00815   0.00276  -0.0271   0.1578   1.0000
   5.250   0.7072   0.00853   0.00301  -0.0260   0.1282   1.0000
   5.500   0.7288   0.00894   0.00327  -0.0249   0.0994   1.0000
   5.750   0.7506   0.00937   0.00357  -0.0239   0.0735   1.0000
   6.000   0.7716   0.00990   0.00393  -0.0228   0.0443   1.0000
   6.250   0.7914   0.01062   0.00446  -0.0214   0.0157   1.0000
   6.500   0.8143   0.01104   0.00487  -0.0205   0.0125   1.0000
   6.750   0.8380   0.01139   0.00526  -0.0197   0.0116   1.0000
   7.000   0.8614   0.01179   0.00569  -0.0190   0.0107   1.0000
   7.250   0.8839   0.01232   0.00627  -0.0181   0.0098   1.0000
   7.500   0.9054   0.01298   0.00701  -0.0170   0.0093   1.0000
   7.750   0.9283   0.01345   0.00753  -0.0162   0.0090   1.0000
   8.000   0.9506   0.01399   0.00813  -0.0153   0.0089   1.0000
   8.250   0.9726   0.01455   0.00875  -0.0144   0.0087   1.0000
   8.500   0.9938   0.01518   0.00945  -0.0135   0.0085   1.0000
   8.750   1.0145   0.01584   0.01018  -0.0124   0.0083   1.0000
   9.000   1.0344   0.01658   0.01099  -0.0113   0.0081   1.0000
   9.250   1.0542   0.01729   0.01175  -0.0102   0.0078   1.0000
   9.500   1.0727   0.01811   0.01264  -0.0089   0.0077   1.0000
   9.750   1.0905   0.01896   0.01355  -0.0076   0.0074   1.0000
  10.000   1.1067   0.01993   0.01460  -0.0061   0.0073   1.0000
  10.250   1.1211   0.02104   0.01579  -0.0044   0.0071   1.0000
  10.500   1.1287   0.02290   0.01775  -0.0019   0.0069   1.0000
  10.750   1.1403   0.02428   0.01924   0.0000   0.0069   1.0000
  11.000   1.1518   0.02547   0.02053   0.0020   0.0069   1.0000
  11.250   1.1510   0.02816   0.02340   0.0053   0.0067   1.0000
  11.500   1.1523   0.02979   0.02521   0.0083   0.0066   1.0000
  11.750   1.1555   0.03114   0.02670   0.0108   0.0066   1.0000
  12.000   1.1570   0.03280   0.02850   0.0130   0.0065   1.0000
  12.250   1.1564   0.03474   0.03058   0.0150   0.0065   1.0000
  12.500   1.1579   0.03633   0.03232   0.0164   0.0064   1.0000
  12.750   1.1514   0.03924   0.03538   0.0177   0.0065   1.0000
  13.000   1.1441   0.04228   0.03860   0.0183   0.0064   1.0000
  13.250   1.1367   0.04555   0.04202   0.0183   0.0064   1.0000
  13.500   1.1220   0.05012   0.04678   0.0175   0.0065   1.0000
  13.750   1.1158   0.05377   0.05056   0.0161   0.0064   1.0000
  14.000   1.0962   0.05976   0.05673   0.0136   0.0065   1.0000
  14.250   1.0815   0.06547   0.06260   0.0106   0.0065   1.0000
  14.500   1.0653   0.07185   0.06913   0.0069   0.0065   1.0000
  15.250   1.0224   0.09221   0.08981  -0.0050   0.0068   1.0000
  15.500   1.0072   0.10013   0.09786  -0.0101   0.0068   1.0000
  15.750   0.9872   0.10954   0.10739  -0.0162   0.0068   1.0000
  16.000   0.9841   0.11556   0.11349  -0.0200   0.0069   1.0000
  16.250   0.9648   0.12569   0.12374  -0.0262   0.0069   1.0000
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