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E231 (e231-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E231 (e231-il)
Reynolds number: 100,000
Max Cl/Cd: 51.1 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e231-il-100000-n5.txt
Download as CSV file: xf-e231-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E231                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2972   0.11045   0.10596  -0.0456   1.0000   0.0212
 -11.000  -0.3673   0.10980   0.10481  -0.0483   1.0000   0.0210
 -10.750  -0.3657   0.10667   0.10173  -0.0488   1.0000   0.0204
 -10.500  -0.3672   0.10325   0.09838  -0.0494   1.0000   0.0198
 -10.250  -0.3721   0.09980   0.09502  -0.0498   1.0000   0.0194
 -10.000  -0.3807   0.09686   0.09216  -0.0494   1.0000   0.0187
  -9.750  -0.3944   0.09440   0.08980  -0.0480   1.0000   0.0183
  -9.500  -0.4035   0.09001   0.08546  -0.0497   0.9968   0.0177
  -9.000  -0.4123   0.07061   0.06594  -0.0695   0.9807   0.0155
  -8.750  -0.4153   0.06594   0.06117  -0.0733   0.9732   0.0153
  -8.500  -0.4200   0.06184   0.05692  -0.0752   0.9651   0.0151
  -8.250  -0.4214   0.05746   0.05234  -0.0766   0.9581   0.0149
  -8.000  -0.4227   0.05409   0.04876  -0.0761   0.9505   0.0147
  -7.750  -0.4200   0.05022   0.04458  -0.0758   0.9445   0.0146
  -7.500  -0.4193   0.04697   0.04102  -0.0740   0.9376   0.0145
  -7.250  -0.4136   0.04367   0.03734  -0.0723   0.9319   0.0144
  -7.000  -0.4035   0.04051   0.03375  -0.0709   0.9273   0.0143
  -6.750  -0.3972   0.03805   0.03089  -0.0680   0.9207   0.0146
  -6.500  -0.3811   0.03542   0.02759  -0.0662   0.9166   0.0156
  -6.250  -0.3642   0.03333   0.02512  -0.0647   0.9125   0.0157
  -6.000  -0.3516   0.03199   0.02369  -0.0631   0.9070   0.0175
  -5.750  -0.3290   0.03028   0.02166  -0.0623   0.9036   0.0186
  -5.500  -0.3014   0.02827   0.01927  -0.0621   0.9012   0.0194
  -5.250  -0.2826   0.02701   0.01779  -0.0604   0.8964   0.0199
  -5.000  -0.2596   0.02566   0.01623  -0.0593   0.8924   0.0209
  -4.750  -0.2337   0.02449   0.01491  -0.0588   0.8894   0.0221
  -4.500  -0.2086   0.02338   0.01375  -0.0586   0.8869   0.0254
  -4.250  -0.1945   0.02296   0.01320  -0.0560   0.8810   0.0303
  -4.000  -0.1756   0.02207   0.01229  -0.0545   0.8767   0.0363
  -3.750  -0.1514   0.02127   0.01146  -0.0537   0.8738   0.0535
  -3.500  -0.1365   0.02042   0.01091  -0.0515   0.8689   0.0993
  -3.250  -0.1231   0.01935   0.01060  -0.0494   0.8638   0.2465
  -3.000  -0.1106   0.01786   0.01040  -0.0467   0.8603   0.5264
  -2.750  -0.0453   0.01813   0.01154  -0.0507   0.8615   0.8218
  -2.500  -0.0162   0.01857   0.01178  -0.0498   0.8590   0.8668
  -2.250   0.0242   0.01906   0.01203  -0.0513   0.8565   0.8939
  -2.000   0.0606   0.01945   0.01223  -0.0526   0.8526   0.9144
  -1.750   0.1122   0.01964   0.01221  -0.0570   0.8507   0.9286
  -1.500   0.1652   0.01968   0.01204  -0.0620   0.8490   0.9389
  -1.250   0.2111   0.01962   0.01183  -0.0657   0.8468   0.9478
  -1.000   0.2498   0.01955   0.01163  -0.0679   0.8444   0.9568
  -0.750   0.2890   0.01955   0.01154  -0.0707   0.8395   0.9636
  -0.500   0.3222   0.01953   0.01144  -0.0722   0.8349   0.9710
  -0.250   0.3634   0.01930   0.01114  -0.0751   0.8316   0.9757
   0.000   0.3963   0.01925   0.01103  -0.0766   0.8268   0.9817
   0.250   0.4305   0.01915   0.01089  -0.0783   0.8208   0.9864
   0.500   0.4672   0.01890   0.01061  -0.0803   0.8168   0.9906
   0.750   0.4981   0.01886   0.01057  -0.0814   0.8098   0.9953
   1.000   0.5327   0.01863   0.01033  -0.0830   0.8042   0.9992
   1.250   0.5547   0.01861   0.01031  -0.0821   0.7971   1.0000
   1.500   0.5750   0.01853   0.01025  -0.0807   0.7897   1.0000
   1.750   0.5928   0.01856   0.01029  -0.0790   0.7813   1.0000
   2.000   0.6154   0.01838   0.01011  -0.0778   0.7744   1.0000
   2.250   0.6315   0.01844   0.01021  -0.0758   0.7646   1.0000
   2.500   0.6556   0.01819   0.00997  -0.0748   0.7579   1.0000
   2.750   0.6720   0.01820   0.01007  -0.0727   0.7474   1.0000
   3.000   0.6892   0.01818   0.01010  -0.0707   0.7370   1.0000
   3.250   0.7097   0.01803   0.00998  -0.0691   0.7274   1.0000
   3.500   0.7309   0.01783   0.00983  -0.0676   0.7173   1.0000
   3.750   0.7473   0.01780   0.00989  -0.0654   0.7046   1.0000
   4.000   0.7646   0.01772   0.00987  -0.0632   0.6911   1.0000
   4.250   0.7825   0.01762   0.00983  -0.0612   0.6768   1.0000
   4.500   0.8018   0.01748   0.00974  -0.0593   0.6612   1.0000
   4.750   0.8174   0.01748   0.00983  -0.0569   0.6429   1.0000
   5.000   0.8349   0.01742   0.00979  -0.0547   0.6228   1.0000
   5.250   0.8527   0.01737   0.00976  -0.0525   0.5998   1.0000
   5.500   0.8705   0.01736   0.00972  -0.0503   0.5732   1.0000
   5.750   0.8866   0.01744   0.00974  -0.0479   0.5427   1.0000
   6.000   0.9009   0.01763   0.00985  -0.0452   0.5094   1.0000
   6.250   0.9123   0.01794   0.01003  -0.0421   0.4756   1.0000
   6.500   0.9207   0.01836   0.01032  -0.0385   0.4424   1.0000
   6.750   0.9271   0.01883   0.01067  -0.0347   0.4113   1.0000
   7.000   0.9318   0.01935   0.01107  -0.0307   0.3819   1.0000
   7.250   0.9361   0.01989   0.01152  -0.0267   0.3551   1.0000
   7.500   0.9388   0.02045   0.01200  -0.0224   0.3301   1.0000
   7.750   0.9408   0.02102   0.01249  -0.0181   0.3071   1.0000
   8.000   0.9450   0.02164   0.01304  -0.0144   0.2840   1.0000
   8.250   0.9502   0.02235   0.01368  -0.0110   0.2616   1.0000
   8.500   0.9575   0.02310   0.01438  -0.0082   0.2398   1.0000
   8.750   0.9650   0.02393   0.01516  -0.0055   0.2198   1.0000
   9.000   0.9739   0.02477   0.01599  -0.0031   0.2000   1.0000
   9.250   0.9827   0.02568   0.01688  -0.0009   0.1824   1.0000
   9.500   0.9906   0.02670   0.01790   0.0013   0.1655   1.0000
   9.750   0.9998   0.02771   0.01891   0.0033   0.1497   1.0000
  10.000   1.0087   0.02878   0.02001   0.0051   0.1354   1.0000
  10.250   1.0171   0.02994   0.02118   0.0070   0.1225   1.0000
  10.500   1.0245   0.03120   0.02244   0.0088   0.1113   1.0000
  10.750   1.0329   0.03244   0.02377   0.0105   0.1002   1.0000
  11.000   1.0407   0.03377   0.02518   0.0121   0.0898   1.0000
  11.250   1.0472   0.03524   0.02669   0.0137   0.0813   1.0000
  11.500   1.0515   0.03687   0.02834   0.0153   0.0737   1.0000
  11.750   1.0588   0.03840   0.03007   0.0166   0.0661   1.0000
  12.000   1.0612   0.04031   0.03200   0.0181   0.0602   1.0000
  12.250   1.0667   0.04206   0.03391   0.0193   0.0535   1.0000
  12.500   1.0672   0.04424   0.03612   0.0206   0.0487   1.0000
  12.750   1.0707   0.04628   0.03835   0.0216   0.0429   1.0000
  13.000   1.0679   0.04887   0.04097   0.0225   0.0392   1.0000
  13.250   1.0702   0.05124   0.04355   0.0234   0.0355   1.0000
  13.500   1.0690   0.05389   0.04634   0.0238   0.0319   1.0000
  13.750   1.0633   0.05713   0.04962   0.0241   0.0297   1.0000
  14.000   1.0623   0.06017   0.05290   0.0245   0.0273   1.0000
  14.250   1.0585   0.06356   0.05648   0.0243   0.0248   1.0000
  14.500   1.0535   0.06718   0.06023   0.0238   0.0234   1.0000
  14.750   1.0448   0.07143   0.06455   0.0228   0.0220   1.0000
  15.000   1.0387   0.07565   0.06897   0.0219   0.0209   1.0000
  15.250   1.0319   0.08020   0.07376   0.0208   0.0200   1.0000
  15.500   1.0227   0.08527   0.07906   0.0192   0.0192   1.0000
  15.750   1.0119   0.09083   0.08482   0.0168   0.0182   1.0000
  16.000   1.0008   0.09667   0.09088   0.0143   0.0178   1.0000
  16.250   0.9893   0.10281   0.09721   0.0113   0.0176   1.0000
  16.500   0.9759   0.10962   0.10418   0.0078   0.0172   1.0000
  16.750   0.9625   0.11667   0.11136   0.0037   0.0166   1.0000
  17.000   0.9451   0.12508   0.11994  -0.0008   0.0170   1.0000
  17.250   0.9192   0.13617   0.13127  -0.0069   0.0180   1.0000
  17.500   0.8921   0.14845   0.14368  -0.0137   0.0189   1.0000
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