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E64 (8.45%) (e64-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E64 (8.45%) (e64-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.66 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e64-il-1000000.txt
Download as CSV file: xf-e64-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E64  (8.45%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4014   0.10244   0.10081  -0.0282   1.0000   0.0086
  -9.250  -0.4030   0.09907   0.09746  -0.0285   1.0000   0.0091
  -9.000  -0.4061   0.09564   0.09405  -0.0288   1.0000   0.0094
  -8.750  -0.3108   0.07233   0.07085  -0.0421   0.9963   0.0101
  -8.500  -0.3047   0.06769   0.06622  -0.0451   0.9954   0.0103
  -8.250  -0.2972   0.06366   0.06219  -0.0479   0.9941   0.0105
  -8.000  -0.2925   0.05897   0.05751  -0.0512   0.9919   0.0106
  -7.750  -0.2871   0.05384   0.05238  -0.0555   0.9892   0.0107
  -7.500  -0.2800   0.04841   0.04695  -0.0611   0.9866   0.0109
  -7.250  -0.2701   0.04210   0.04065  -0.0699   0.9829   0.0111
  -7.000  -0.2604   0.03125   0.02970  -0.0866   0.9768   0.0111
  -6.750  -0.2415   0.02186   0.02005  -0.0978   0.9743   0.0114
  -6.500  -0.2167   0.01534   0.01320  -0.1046   0.9729   0.0122
  -6.250  -0.1933   0.01256   0.01006  -0.1060   0.9681   0.0137
  -6.000  -0.1674   0.01024   0.00737  -0.1081   0.9645   0.0138
  -5.250  -0.1030   0.01361   0.00916  -0.1147   0.9614   0.0101
  -5.000  -0.0707   0.01170   0.00708  -0.1159   0.9598   0.0093
  -4.750  -0.0441   0.01072   0.00597  -0.1156   0.9550   0.0094
  -4.500  -0.0143   0.01015   0.00532  -0.1159   0.9510   0.0097
  -4.250   0.0163   0.00894   0.00398  -0.1167   0.9477   0.0104
  -4.000   0.0465   0.00838   0.00335  -0.1173   0.9435   0.0110
  -3.750   0.0743   0.00797   0.00290  -0.1173   0.9373   0.0114
  -3.500   0.1057   0.00764   0.00251  -0.1180   0.9326   0.0123
  -3.250   0.1332   0.00737   0.00219  -0.1178   0.9252   0.0131
  -3.000   0.1632   0.00711   0.00185  -0.1182   0.9190   0.0137
  -2.750   0.1910   0.00685   0.00154  -0.1180   0.9111   0.0174
  -2.500   0.2199   0.00634   0.00129  -0.1184   0.9041   0.0933
  -2.250   0.2470   0.00602   0.00117  -0.1183   0.8953   0.1619
  -2.000   0.2749   0.00572   0.00108  -0.1185   0.8870   0.2418
  -1.750   0.3024   0.00548   0.00102  -0.1185   0.8775   0.3148
  -1.500   0.3298   0.00525   0.00098  -0.1185   0.8676   0.3914
  -1.250   0.3572   0.00506   0.00095  -0.1185   0.8578   0.4663
  -1.000   0.3845   0.00490   0.00094  -0.1184   0.8472   0.5404
  -0.750   0.4116   0.00480   0.00094  -0.1182   0.8354   0.5917
  -0.500   0.4386   0.00472   0.00094  -0.1179   0.8229   0.6430
  -0.250   0.4653   0.00465   0.00096  -0.1176   0.8096   0.6931
   0.000   0.4917   0.00460   0.00098  -0.1172   0.7960   0.7445
   0.250   0.5176   0.00456   0.00102  -0.1166   0.7818   0.7909
   0.500   0.5428   0.00454   0.00106  -0.1159   0.7664   0.8341
   0.750   0.5667   0.00454   0.00110  -0.1149   0.7497   0.8766
   1.000   0.5883   0.00454   0.00113  -0.1132   0.7324   0.9216
   1.250   0.6152   0.00453   0.00112  -0.1128   0.7133   0.9825
   1.500   0.6431   0.00465   0.00115  -0.1128   0.6930   1.0000
   1.750   0.6695   0.00479   0.00121  -0.1125   0.6724   1.0000
   2.000   0.6957   0.00495   0.00127  -0.1121   0.6496   1.0000
   2.250   0.7216   0.00513   0.00134  -0.1117   0.6248   1.0000
   2.500   0.7472   0.00533   0.00144  -0.1112   0.5974   1.0000
   2.750   0.7726   0.00555   0.00155  -0.1107   0.5673   1.0000
   3.000   0.7980   0.00578   0.00166  -0.1103   0.5381   1.0000
   3.250   0.8233   0.00603   0.00179  -0.1098   0.5079   1.0000
   3.500   0.8477   0.00636   0.00196  -0.1092   0.4669   1.0000
   3.750   0.8697   0.00690   0.00219  -0.1082   0.4008   1.0000
   4.000   0.8923   0.00743   0.00243  -0.1074   0.3394   1.0000
   4.250   0.9162   0.00785   0.00266  -0.1067   0.2970   1.0000
   4.500   0.9400   0.00828   0.00292  -0.1061   0.2573   1.0000
   4.750   0.9631   0.00878   0.00321  -0.1054   0.2121   1.0000
   5.000   0.9864   0.00927   0.00351  -0.1047   0.1730   1.0000
   5.250   1.0091   0.00981   0.00384  -0.1039   0.1337   1.0000
   5.500   1.0314   0.01040   0.00423  -0.1030   0.0946   1.0000
   5.750   1.0526   0.01112   0.00470  -0.1020   0.0519   1.0000
   6.000   1.0724   0.01199   0.00532  -0.1007   0.0158   1.0000
   6.250   1.0965   0.01240   0.00574  -0.1000   0.0126   1.0000
   6.500   1.1204   0.01282   0.00620  -0.0993   0.0115   1.0000
   6.750   1.1436   0.01330   0.00672  -0.0985   0.0106   1.0000
   7.000   1.1654   0.01395   0.00747  -0.0974   0.0098   1.0000
   7.250   1.1877   0.01451   0.00810  -0.0965   0.0095   1.0000
   7.500   1.2101   0.01503   0.00868  -0.0956   0.0092   1.0000
   7.750   1.2317   0.01562   0.00933  -0.0945   0.0088   1.0000
   8.000   1.2522   0.01630   0.01008  -0.0933   0.0085   1.0000
   8.250   1.2721   0.01702   0.01087  -0.0920   0.0083   1.0000
   8.500   1.2910   0.01781   0.01174  -0.0906   0.0082   1.0000
   8.750   1.3091   0.01864   0.01266  -0.0890   0.0080   1.0000
   9.000   1.3263   0.01954   0.01364  -0.0873   0.0078   1.0000
   9.250   1.3428   0.02047   0.01465  -0.0856   0.0076   1.0000
   9.500   1.3582   0.02147   0.01573  -0.0837   0.0074   1.0000
   9.750   1.3718   0.02261   0.01695  -0.0816   0.0073   1.0000
  10.000   1.3822   0.02391   0.01834  -0.0790   0.0071   1.0000
  10.250   1.3899   0.02562   0.02016  -0.0760   0.0069   1.0000
  10.500   1.3967   0.02793   0.02262  -0.0732   0.0068   1.0000
  10.750   1.4020   0.03136   0.02631  -0.0705   0.0066   1.0000
  11.000   1.4106   0.03159   0.02664  -0.0677   0.0064   1.0000
  11.250   1.4178   0.03279   0.02799  -0.0651   0.0063   1.0000
  11.500   1.4225   0.03445   0.02981  -0.0624   0.0062   1.0000
  11.750   1.4247   0.03643   0.03195  -0.0597   0.0062   1.0000
  12.000   1.4244   0.03866   0.03437  -0.0570   0.0061   1.0000
  12.250   1.4216   0.04119   0.03708  -0.0544   0.0061   1.0000
  12.500   1.4170   0.04391   0.03999  -0.0521   0.0060   1.0000
  12.750   1.4095   0.04706   0.04333  -0.0501   0.0060   1.0000
  13.000   1.3991   0.05070   0.04718  -0.0486   0.0060   1.0000
  13.250   1.3879   0.05460   0.05127  -0.0477   0.0060   1.0000
  13.500   1.3737   0.05919   0.05605  -0.0474   0.0060   1.0000
  13.750   1.3588   0.06419   0.06124  -0.0480   0.0060   1.0000
  14.000   1.3411   0.07006   0.06730  -0.0496   0.0060   1.0000
  14.250   1.3235   0.07642   0.07384  -0.0520   0.0060   1.0000
  14.500   1.3034   0.08383   0.08143  -0.0556   0.0060   1.0000
  14.750   1.2830   0.09206   0.08983  -0.0601   0.0061   1.0000
  15.000   1.2621   0.10111   0.09904  -0.0656   0.0061   1.0000
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