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E210 (13.64%) (e210-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E210 (13.64%) (e210-il)
Reynolds number: 100,000
Max Cl/Cd: 57.08 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e210-il-100000-n5.txt
Download as CSV file: xf-e210-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E210  (13.64%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4156   0.07970   0.07508  -0.0533   1.0000   0.0303
  -9.000  -0.4321   0.07512   0.07058  -0.0539   1.0000   0.0300
  -8.750  -0.4578   0.07034   0.06588  -0.0546   1.0000   0.0298
  -8.500  -0.4805   0.06407   0.05959  -0.0604   0.9953   0.0295
  -8.250  -0.4801   0.05401   0.04906  -0.0749   0.9827   0.0294
  -8.000  -0.4708   0.04704   0.04151  -0.0820   0.9723   0.0295
  -7.750  -0.4560   0.04178   0.03562  -0.0858   0.9623   0.0298
  -7.500  -0.4342   0.03758   0.03076  -0.0885   0.9539   0.0302
  -7.250  -0.4065   0.03492   0.02789  -0.0909   0.9471   0.0314
  -7.000  -0.3805   0.03326   0.02606  -0.0920   0.9383   0.0332
  -6.750  -0.3478   0.03106   0.02349  -0.0943   0.9325   0.0349
  -6.500  -0.3218   0.02901   0.02107  -0.0947   0.9230   0.0360
  -6.250  -0.2867   0.02708   0.01879  -0.0965   0.9180   0.0374
  -6.000  -0.2603   0.02560   0.01716  -0.0966   0.9081   0.0389
  -5.750  -0.2275   0.02445   0.01599  -0.0981   0.9013   0.0419
  -5.500  -0.1972   0.02335   0.01474  -0.0987   0.8927   0.0448
  -5.250  -0.1653   0.02224   0.01347  -0.0995   0.8849   0.0474
  -5.000  -0.1327   0.02110   0.01233  -0.1007   0.8769   0.0510
  -4.750  -0.1008   0.02028   0.01140  -0.1016   0.8674   0.0579
  -4.500  -0.0635   0.01930   0.01039  -0.1037   0.8603   0.0704
  -4.250  -0.0314   0.01839   0.00956  -0.1049   0.8495   0.0918
  -4.000   0.0044   0.01756   0.00884  -0.1068   0.8403   0.1341
  -3.750   0.0400   0.01666   0.00824  -0.1089   0.8307   0.2114
  -3.500   0.0721   0.01588   0.00787  -0.1102   0.8190   0.3120
  -3.250   0.1057   0.01550   0.00770  -0.1113   0.8078   0.3967
  -3.000   0.1408   0.01535   0.00750  -0.1124   0.7970   0.4550
  -2.750   0.1740   0.01529   0.00732  -0.1132   0.7850   0.4955
  -2.500   0.2047   0.01527   0.00721  -0.1135   0.7725   0.5257
  -2.250   0.2352   0.01525   0.00710  -0.1137   0.7605   0.5502
  -2.000   0.2664   0.01524   0.00696  -0.1141   0.7491   0.5728
  -1.750   0.2972   0.01523   0.00685  -0.1144   0.7383   0.5921
  -1.500   0.3249   0.01526   0.00679  -0.1142   0.7266   0.6097
  -1.250   0.3532   0.01528   0.00673  -0.1140   0.7159   0.6268
  -1.000   0.3824   0.01530   0.00665  -0.1141   0.7063   0.6430
  -0.750   0.4092   0.01534   0.00662  -0.1138   0.6959   0.6579
  -0.500   0.4366   0.01538   0.00660  -0.1135   0.6865   0.6727
  -0.250   0.4645   0.01543   0.00655  -0.1134   0.6778   0.6875
   0.000   0.4904   0.01549   0.00659  -0.1129   0.6684   0.7022
   0.250   0.5185   0.01555   0.00656  -0.1128   0.6607   0.7169
   0.500   0.5440   0.01562   0.00663  -0.1123   0.6516   0.7319
   0.750   0.5711   0.01569   0.00665  -0.1120   0.6444   0.7477
   1.000   0.5960   0.01576   0.00674  -0.1114   0.6361   0.7649
   1.250   0.6220   0.01583   0.00678  -0.1108   0.6292   0.7842
   1.500   0.6458   0.01591   0.00690  -0.1099   0.6213   0.8069
   1.750   0.6708   0.01595   0.00693  -0.1091   0.6151   0.8338
   2.000   0.6928   0.01599   0.00706  -0.1078   0.6073   0.8693
   2.250   0.7228   0.01601   0.00708  -0.1080   0.6011   0.9211
   2.500   0.7569   0.01614   0.00721  -0.1096   0.5934   1.0000
   2.750   0.7858   0.01637   0.00736  -0.1101   0.5870   1.0000
   3.000   0.8129   0.01664   0.00759  -0.1102   0.5802   1.0000
   3.250   0.8401   0.01689   0.00780  -0.1103   0.5736   1.0000
   3.500   0.8679   0.01716   0.00802  -0.1105   0.5677   1.0000
   3.750   0.8934   0.01745   0.00833  -0.1103   0.5606   1.0000
   4.000   0.9215   0.01771   0.00853  -0.1105   0.5551   1.0000
   4.250   0.9460   0.01803   0.00890  -0.1100   0.5481   1.0000
   4.500   0.9726   0.01831   0.00919  -0.1100   0.5419   1.0000
   4.750   0.9984   0.01862   0.00952  -0.1097   0.5358   1.0000
   5.000   1.0230   0.01894   0.00989  -0.1093   0.5290   1.0000
   5.250   1.0507   0.01923   0.01017  -0.1094   0.5235   1.0000
   5.500   1.0728   0.01959   0.01065  -0.1085   0.5159   1.0000
   5.750   1.0992   0.01988   0.01094  -0.1084   0.5098   1.0000
   6.000   1.1215   0.02024   0.01141  -0.1075   0.5022   1.0000
   6.250   1.1466   0.02052   0.01174  -0.1071   0.4951   1.0000
   6.500   1.1682   0.02087   0.01220  -0.1061   0.4869   1.0000
   6.750   1.1927   0.02113   0.01248  -0.1056   0.4792   1.0000
   7.000   1.2126   0.02149   0.01297  -0.1043   0.4701   1.0000
   7.250   1.2360   0.02175   0.01329  -0.1035   0.4619   1.0000
   7.500   1.2551   0.02210   0.01377  -0.1021   0.4521   1.0000
   7.750   1.2748   0.02244   0.01421  -0.1008   0.4424   1.0000
   8.000   1.2957   0.02270   0.01451  -0.0996   0.4328   1.0000
   8.250   1.3119   0.02309   0.01506  -0.0977   0.4212   1.0000
   8.500   1.3282   0.02347   0.01556  -0.0958   0.4095   1.0000
   8.750   1.3437   0.02386   0.01604  -0.0938   0.3974   1.0000
   9.000   1.3579   0.02428   0.01654  -0.0916   0.3845   1.0000
   9.250   1.3690   0.02473   0.01706  -0.0889   0.3709   1.0000
   9.500   1.3782   0.02527   0.01770  -0.0860   0.3566   1.0000
   9.750   1.3858   0.02592   0.01842  -0.0830   0.3409   1.0000
  10.000   1.3920   0.02668   0.01924  -0.0799   0.3238   1.0000
  10.250   1.3963   0.02759   0.02018  -0.0767   0.3052   1.0000
  10.500   1.3986   0.02868   0.02126  -0.0736   0.2861   1.0000
  10.750   1.3992   0.02999   0.02258  -0.0705   0.2653   1.0000
  11.000   1.3971   0.03158   0.02413  -0.0674   0.2450   1.0000
  11.250   1.3933   0.03345   0.02599  -0.0646   0.2256   1.0000
  11.500   1.3886   0.03559   0.02810  -0.0621   0.2071   1.0000
  11.750   1.3826   0.03802   0.03051  -0.0599   0.1905   1.0000
  12.000   1.3763   0.04069   0.03317  -0.0581   0.1755   1.0000
  12.250   1.3700   0.04357   0.03606  -0.0567   0.1619   1.0000
  12.500   1.3637   0.04662   0.03914  -0.0556   0.1494   1.0000
  12.750   1.3574   0.04985   0.04241  -0.0548   0.1383   1.0000
  13.000   1.3504   0.05330   0.04588  -0.0543   0.1286   1.0000
  13.250   1.3446   0.05678   0.04941  -0.0540   0.1188   1.0000
  13.500   1.3397   0.06028   0.05298  -0.0539   0.1101   1.0000
  13.750   1.3326   0.06415   0.05686  -0.0540   0.1028   1.0000
  14.000   1.3288   0.06776   0.06057  -0.0542   0.0948   1.0000
  14.250   1.3231   0.07169   0.06453  -0.0546   0.0885   1.0000
  14.500   1.3189   0.07554   0.06851  -0.0551   0.0819   1.0000
  14.750   1.3136   0.07962   0.07262  -0.0558   0.0764   1.0000
  15.000   1.3098   0.08362   0.07674  -0.0566   0.0704   1.0000
  15.250   1.3035   0.08802   0.08114  -0.0576   0.0658   1.0000
  15.500   1.3007   0.09207   0.08535  -0.0586   0.0601   1.0000
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