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E64 (8.45%) (e64-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E64 (8.45%) (e64-il)
Reynolds number: 500,000
Max Cl/Cd: 120.58 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e64-il-500000.txt
Download as CSV file: xf-e64-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3204   0.08827   0.08622  -0.0300   1.0000   0.0181
  -8.750  -0.3289   0.08482   0.08280  -0.0303   1.0000   0.0188
  -8.500  -0.3356   0.08195   0.07997  -0.0298   1.0000   0.0190
  -8.250  -0.3351   0.07758   0.07561  -0.0323   0.9991   0.0191
  -8.000  -0.3295   0.07224   0.07028  -0.0363   0.9972   0.0192
  -7.750  -0.3351   0.06422   0.06228  -0.0407   0.9952   0.0197
  -7.500  -0.3258   0.06068   0.05874  -0.0427   0.9925   0.0202
  -7.250  -0.3173   0.05652   0.05458  -0.0462   0.9888   0.0206
  -7.000  -0.3049   0.05118   0.04924  -0.0528   0.9855   0.0211
  -6.750  -0.2937   0.04520   0.04325  -0.0612   0.9799   0.0216
  -6.500  -0.2763   0.03720   0.03517  -0.0731   0.9756   0.0222
  -6.250  -0.2531   0.02883   0.02658  -0.0840   0.9731   0.0235
  -6.000  -0.2289   0.02373   0.02103  -0.0894   0.9674   0.0261
  -5.750  -0.2113   0.01546   0.01222  -0.0956   0.9634   0.0275
  -5.500  -0.1814   0.01317   0.00990  -0.0981   0.9617   0.0288
  -5.250  -0.1485   0.01092   0.00742  -0.1010   0.9603   0.0313
  -5.000  -0.1077   0.01108   0.00720  -0.1029   0.9593   0.0356
  -4.750  -0.1122   0.01612   0.01086  -0.1033   0.9606   0.0160
  -4.500  -0.0756   0.01399   0.00837  -0.1048   0.9596   0.0150
  -4.250  -0.0487   0.01298   0.00726  -0.1046   0.9546   0.0155
  -4.000  -0.0154   0.01211   0.00631  -0.1058   0.9517   0.0161
  -3.750   0.0205   0.01147   0.00561  -0.1075   0.9499   0.0175
  -3.500   0.0577   0.01081   0.00489  -0.1095   0.9484   0.0185
  -3.250   0.0950   0.01018   0.00418  -0.1114   0.9470   0.0191
  -3.000   0.1295   0.00953   0.00345  -0.1127   0.9443   0.0224
  -2.750   0.1586   0.00899   0.00299  -0.1129   0.9386   0.0506
  -2.500   0.1924   0.00816   0.00268  -0.1145   0.9352   0.1885
  -2.250   0.2274   0.00762   0.00247  -0.1163   0.9324   0.2941
  -2.000   0.2546   0.00727   0.00235  -0.1162   0.9252   0.3781
  -1.750   0.2865   0.00682   0.00224  -0.1172   0.9202   0.4886
  -1.500   0.3155   0.00654   0.00216  -0.1174   0.9135   0.5684
  -1.250   0.3446   0.00628   0.00209  -0.1175   0.9064   0.6432
  -1.000   0.3723   0.00610   0.00204  -0.1172   0.8981   0.7016
  -0.750   0.4006   0.00592   0.00198  -0.1170   0.8902   0.7593
  -0.500   0.4249   0.00579   0.00198  -0.1159   0.8799   0.8132
  -0.250   0.4488   0.00567   0.00195  -0.1146   0.8700   0.8638
   0.000   0.4711   0.00557   0.00189  -0.1129   0.8597   0.9136
   0.250   0.5005   0.00546   0.00179  -0.1128   0.8483   0.9713
   0.500   0.5326   0.00546   0.00172  -0.1136   0.8357   1.0000
   0.750   0.5602   0.00552   0.00170  -0.1135   0.8226   1.0000
   1.000   0.5877   0.00558   0.00169  -0.1133   0.8088   1.0000
   1.250   0.6148   0.00566   0.00170  -0.1131   0.7940   1.0000
   1.500   0.6417   0.00575   0.00172  -0.1128   0.7780   1.0000
   1.750   0.6683   0.00586   0.00175  -0.1124   0.7609   1.0000
   2.000   0.6946   0.00596   0.00179  -0.1120   0.7422   1.0000
   2.250   0.7207   0.00610   0.00185  -0.1115   0.7226   1.0000
   2.500   0.7465   0.00625   0.00193  -0.1110   0.7018   1.0000
   2.750   0.7719   0.00642   0.00202  -0.1104   0.6784   1.0000
   3.000   0.7970   0.00661   0.00212  -0.1098   0.6528   1.0000
   3.250   0.8216   0.00683   0.00224  -0.1091   0.6246   1.0000
   3.500   0.8461   0.00708   0.00240  -0.1083   0.5954   1.0000
   3.750   0.8702   0.00735   0.00256  -0.1076   0.5647   1.0000
   4.000   0.8935   0.00768   0.00275  -0.1067   0.5273   1.0000
   4.250   0.9151   0.00813   0.00297  -0.1055   0.4758   1.0000
   4.500   0.9359   0.00868   0.00326  -0.1042   0.4169   1.0000
   4.750   0.9573   0.00925   0.00356  -0.1032   0.3605   1.0000
   5.000   0.9783   0.00988   0.00391  -0.1021   0.3026   1.0000
   5.250   1.0001   0.01047   0.00428  -0.1011   0.2527   1.0000
   5.500   1.0220   0.01106   0.00468  -0.1003   0.2091   1.0000
   5.750   1.0438   0.01167   0.00510  -0.0994   0.1684   1.0000
   6.000   1.0646   0.01240   0.00558  -0.0983   0.1234   1.0000
   6.250   1.0843   0.01324   0.00615  -0.0971   0.0776   1.0000
   6.500   1.1008   0.01445   0.00700  -0.0954   0.0259   1.0000
   6.750   1.1221   0.01516   0.00770  -0.0942   0.0187   1.0000
   7.000   1.1443   0.01573   0.00834  -0.0932   0.0170   1.0000
   7.250   1.1655   0.01639   0.00906  -0.0921   0.0157   1.0000
   7.500   1.1849   0.01724   0.00999  -0.0906   0.0146   1.0000
   7.750   1.2008   0.01841   0.01131  -0.0886   0.0139   1.0000
   8.000   1.2177   0.01944   0.01243  -0.0868   0.0136   1.0000
   8.250   1.2355   0.02033   0.01342  -0.0852   0.0133   1.0000
   8.500   1.2526   0.02129   0.01447  -0.0834   0.0129   1.0000
   8.750   1.2688   0.02234   0.01563  -0.0816   0.0124   1.0000
   9.000   1.2838   0.02357   0.01697  -0.0797   0.0123   1.0000
   9.250   1.2983   0.02489   0.01839  -0.0777   0.0120   1.0000
   9.500   1.3124   0.02630   0.01994  -0.0756   0.0118   1.0000
   9.750   1.3265   0.02786   0.02165  -0.0736   0.0117   1.0000
  10.000   1.3404   0.02957   0.02351  -0.0717   0.0115   1.0000
  10.250   1.3537   0.03151   0.02562  -0.0698   0.0114   1.0000
  10.500   1.3656   0.03383   0.02817  -0.0677   0.0114   1.0000
  10.750   1.3740   0.03673   0.03136  -0.0653   0.0115   1.0000
  11.000   1.3757   0.04011   0.03509  -0.0621   0.0118   1.0000
  11.250   1.3720   0.04331   0.03859  -0.0586   0.0120   1.0000
  11.500   1.3643   0.04652   0.04209  -0.0550   0.0120   1.0000
  11.750   1.3534   0.04996   0.04580  -0.0518   0.0121   1.0000
  12.000   1.3386   0.05390   0.05001  -0.0490   0.0123   1.0000
  12.250   1.3197   0.05846   0.05483  -0.0469   0.0125   1.0000
  12.500   1.2991   0.06345   0.06006  -0.0458   0.0128   1.0000
  12.750   1.2763   0.06914   0.06596  -0.0458   0.0130   1.0000
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