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E64 (8.45%) (e64-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E64 (8.45%) (e64-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.24 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e64-il-1000000-n5.txt
Download as CSV file: xf-e64-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4056   0.10731   0.10563  -0.0278   1.0000   0.0052
  -9.750  -0.4055   0.10390   0.10224  -0.0282   1.0000   0.0054
  -9.500  -0.4029   0.10033   0.09868  -0.0295   0.9998   0.0054
  -9.250  -0.3948   0.09578   0.09413  -0.0330   0.9990   0.0051
  -9.000  -0.3855   0.09129   0.08964  -0.0368   0.9978   0.0052
  -8.750  -0.3759   0.08609   0.08444  -0.0414   0.9964   0.0058
  -8.500  -0.3671   0.08169   0.08006  -0.0457   0.9947   0.0052
  -8.250  -0.3596   0.07686   0.07524  -0.0502   0.9919   0.0052
  -8.000  -0.3506   0.07157   0.06995  -0.0560   0.9883   0.0053
  -7.750  -0.3357   0.06508   0.06347  -0.0653   0.9850   0.0053
  -7.500  -0.3514   0.02128   0.01816  -0.1082   0.9651   0.0040
  -7.250  -0.3241   0.01814   0.01456  -0.1102   0.9622   0.0040
  -7.000  -0.2943   0.01607   0.01218  -0.1119   0.9601   0.0041
  -6.750  -0.2701   0.01472   0.01061  -0.1118   0.9545   0.0041
  -6.500  -0.2411   0.01359   0.00929  -0.1126   0.9507   0.0042
  -6.250  -0.2102   0.01264   0.00818  -0.1137   0.9477   0.0043
  -6.000  -0.1818   0.01188   0.00729  -0.1141   0.9430   0.0045
  -5.750  -0.1527   0.01122   0.00652  -0.1146   0.9377   0.0047
  -5.500  -0.1221   0.01058   0.00577  -0.1153   0.9331   0.0050
  -5.250  -0.0943   0.01005   0.00514  -0.1155   0.9265   0.0053
  -5.000  -0.0650   0.00959   0.00458  -0.1159   0.9202   0.0056
  -4.750  -0.0369   0.00916   0.00408  -0.1160   0.9133   0.0058
  -4.500  -0.0085   0.00882   0.00365  -0.1162   0.9060   0.0059
  -4.250   0.0194   0.00851   0.00328  -0.1162   0.8985   0.0061
  -3.750   0.0748   0.00775   0.00236  -0.1162   0.8817   0.0071
  -3.500   0.1026   0.00752   0.00206  -0.1162   0.8725   0.0075
  -3.250   0.1302   0.00734   0.00180  -0.1161   0.8624   0.0079
  -3.000   0.1578   0.00719   0.00158  -0.1160   0.8519   0.0086
  -2.750   0.1854   0.00707   0.00140  -0.1159   0.8417   0.0093
  -2.500   0.2128   0.00698   0.00123  -0.1157   0.8311   0.0107
  -2.000   0.2672   0.00655   0.00096  -0.1155   0.8070   0.0766
  -1.750   0.2943   0.00640   0.00088  -0.1154   0.7938   0.1182
  -1.500   0.3213   0.00623   0.00082  -0.1153   0.7802   0.1733
  -1.250   0.3483   0.00610   0.00078  -0.1152   0.7662   0.2241
  -1.000   0.3750   0.00585   0.00076  -0.1152   0.7514   0.3222
  -0.750   0.4018   0.00577   0.00076  -0.1150   0.7352   0.3751
  -0.500   0.4283   0.00575   0.00076  -0.1148   0.7173   0.4156
  -0.250   0.4549   0.00573   0.00077  -0.1145   0.6979   0.4570
   0.000   0.4814   0.00572   0.00080  -0.1143   0.6788   0.5052
   0.250   0.5079   0.00573   0.00084  -0.1140   0.6594   0.5479
   0.500   0.5343   0.00575   0.00090  -0.1137   0.6383   0.5886
   0.750   0.5603   0.00580   0.00096  -0.1134   0.6145   0.6303
   1.000   0.5862   0.00587   0.00104  -0.1130   0.5897   0.6740
   1.250   0.6120   0.00594   0.00113  -0.1126   0.5638   0.7172
   1.500   0.6376   0.00603   0.00123  -0.1121   0.5381   0.7586
   1.750   0.6628   0.00613   0.00134  -0.1116   0.5129   0.7982
   2.000   0.6872   0.00624   0.00146  -0.1108   0.4854   0.8401
   2.250   0.7100   0.00636   0.00159  -0.1097   0.4565   0.8851
   2.500   0.7301   0.00647   0.00169  -0.1079   0.4272   0.9371
   2.750   0.7576   0.00669   0.00179  -0.1079   0.3914   1.0000
   3.000   0.7831   0.00697   0.00194  -0.1075   0.3611   1.0000
   3.250   0.8087   0.00725   0.00210  -0.1071   0.3319   1.0000
   3.500   0.8311   0.00783   0.00236  -0.1063   0.2656   1.0000
   3.750   0.8531   0.00847   0.00266  -0.1054   0.1975   1.0000
   4.000   0.8767   0.00896   0.00292  -0.1048   0.1530   1.0000
   4.250   0.9014   0.00933   0.00317  -0.1043   0.1266   1.0000
   4.500   0.9259   0.00972   0.00343  -0.1038   0.1008   1.0000
   4.750   0.9502   0.01012   0.00371  -0.1033   0.0771   1.0000
   5.000   0.9735   0.01064   0.00406  -0.1026   0.0475   1.0000
   5.250   0.9969   0.01113   0.00444  -0.1019   0.0260   1.0000
   5.500   1.0202   0.01165   0.00486  -0.1011   0.0100   1.0000
   5.750   1.0451   0.01195   0.00518  -0.1006   0.0087   1.0000
   6.000   1.0699   0.01228   0.00552  -0.1001   0.0080   1.0000
   6.250   1.0943   0.01263   0.00591  -0.0996   0.0074   1.0000
   6.500   1.1183   0.01303   0.00636  -0.0989   0.0069   1.0000
   6.750   1.1422   0.01342   0.00679  -0.0983   0.0067   1.0000
   7.000   1.1660   0.01381   0.00721  -0.0976   0.0066   1.0000
   7.250   1.1894   0.01422   0.00767  -0.0969   0.0064   1.0000
   7.500   1.2124   0.01468   0.00818  -0.0961   0.0062   1.0000
   7.750   1.2349   0.01517   0.00873  -0.0953   0.0060   1.0000
   8.000   1.2570   0.01568   0.00929  -0.0944   0.0058   1.0000
   8.250   1.2788   0.01619   0.00985  -0.0935   0.0055   1.0000
   8.500   1.3000   0.01676   0.01047  -0.0925   0.0053   1.0000
   8.750   1.3204   0.01738   0.01114  -0.0913   0.0051   1.0000
   9.000   1.3403   0.01802   0.01186  -0.0901   0.0050   1.0000
   9.250   1.3594   0.01870   0.01261  -0.0888   0.0049   1.0000
   9.500   1.3772   0.01948   0.01346  -0.0873   0.0047   1.0000
   9.750   1.3936   0.02033   0.01439  -0.0856   0.0046   1.0000
  10.000   1.4077   0.02133   0.01548  -0.0836   0.0045   1.0000
  10.250   1.4176   0.02248   0.01674  -0.0808   0.0044   1.0000
  10.500   1.4223   0.02393   0.01831  -0.0773   0.0043   1.0000
  10.750   1.4316   0.02500   0.01949  -0.0746   0.0042   1.0000
  11.000   1.4421   0.02596   0.02056  -0.0722   0.0042   1.0000
  11.250   1.4522   0.02696   0.02165  -0.0698   0.0042   1.0000
  11.500   1.4605   0.02812   0.02292  -0.0674   0.0041   1.0000
  11.750   1.4679   0.02938   0.02428  -0.0650   0.0041   1.0000
  12.000   1.4752   0.03065   0.02567  -0.0628   0.0040   1.0000
  12.250   1.4797   0.03223   0.02737  -0.0604   0.0040   1.0000
  12.500   1.4835   0.03391   0.02918  -0.0582   0.0039   1.0000
  12.750   1.4866   0.03571   0.03111  -0.0561   0.0039   1.0000
  13.000   1.4872   0.03784   0.03339  -0.0542   0.0038   1.0000
  13.250   1.4876   0.04006   0.03575  -0.0525   0.0038   1.0000
  13.500   1.4861   0.04261   0.03844  -0.0511   0.0037   1.0000
  13.750   1.4835   0.04540   0.04137  -0.0499   0.0037   1.0000
  14.000   1.4808   0.04835   0.04446  -0.0492   0.0036   1.0000
  14.250   1.4753   0.05184   0.04810  -0.0489   0.0035   1.0000
  14.500   1.4698   0.05552   0.05192  -0.0490   0.0035   1.0000
  14.750   1.4626   0.05969   0.05624  -0.0496   0.0034   1.0000
  15.000   1.4530   0.06449   0.06120  -0.0508   0.0034   1.0000
  15.250   1.4424   0.06980   0.06665  -0.0526   0.0034   1.0000
  15.500   1.4296   0.07587   0.07288  -0.0551   0.0033   1.0000
  15.750   1.4153   0.08261   0.07978  -0.0583   0.0033   1.0000
  16.000   1.3996   0.09004   0.08737  -0.0622   0.0033   1.0000
  16.250   1.3818   0.09835   0.09584  -0.0667   0.0033   1.0000
  16.500   1.3629   0.10728   0.10493  -0.0719   0.0033   1.0000
  16.750   1.3418   0.11712   0.11493  -0.0777   0.0033   1.0000
  17.000   1.3207   0.12734   0.12530  -0.0838   0.0033   1.0000
  17.250   1.2996   0.13789   0.13599  -0.0903   0.0033   1.0000
  17.500   1.2769   0.14928   0.14751  -0.0973   0.0034   1.0000
  17.750   1.2547   0.16097   0.15933  -0.1045   0.0034   1.0000
  18.000   1.2306   0.17384   0.17233  -0.1125   0.0034   1.0000
  18.250   1.1978   0.19058   0.18920  -0.1226   0.0035   1.0000
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