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E64 (8.45%) (e64-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E64 (8.45%) (e64-il)
Reynolds number: 100,000
Max Cl/Cd: 63.97 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e64-il-100000.txt
Download as CSV file: xf-e64-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3847   0.10484   0.09987  -0.0325   1.0000   0.0843
  -8.500  -0.3995   0.10364   0.09880  -0.0345   1.0000   0.0857
  -8.250  -0.4200   0.10271   0.09802  -0.0354   1.0000   0.0862
  -8.000  -0.4001   0.09675   0.09204  -0.0328   1.0000   0.0883
  -7.750  -0.3910   0.09378   0.08908  -0.0306   1.0000   0.0910
  -7.500  -0.3947   0.09155   0.08692  -0.0293   1.0000   0.0938
  -7.250  -0.4059   0.08974   0.08522  -0.0278   1.0000   0.0961
  -7.000  -0.4229   0.08799   0.08359  -0.0282   1.0000   0.0985
  -6.750  -0.4436   0.08496   0.08059  -0.0399   1.0000   0.1003
  -6.500  -0.4367   0.08126   0.07700  -0.0321   1.0000   0.1019
  -6.250  -0.4313   0.07899   0.07478  -0.0276   1.0000   0.1048
  -6.000  -0.4305   0.07624   0.07206  -0.0279   1.0000   0.1089
  -5.750  -0.4301   0.07080   0.06652  -0.0392   1.0000   0.1154
  -5.500  -0.4255   0.06889   0.06472  -0.0329   1.0000   0.1184
  -5.250  -0.4144   0.06414   0.05981  -0.0407   1.0000   0.1298
  -5.000  -0.4092   0.06241   0.05818  -0.0354   1.0000   0.1341
  -4.750  -0.3955   0.05850   0.05418  -0.0390   1.0000   0.1462
  -4.500  -0.3789   0.05498   0.05054  -0.0419   1.0000   0.1596
  -4.250  -0.3610   0.05175   0.04719  -0.0439   1.0000   0.1737
  -4.000  -0.3424   0.04876   0.04412  -0.0451   1.0000   0.1883
  -3.750  -0.2425   0.03040   0.02286  -0.0623   1.0000   0.0591
  -3.500  -0.2127   0.02723   0.01933  -0.0634   1.0000   0.0572
  -3.250  -0.1834   0.02503   0.01670  -0.0637   1.0000   0.0563
  -3.000  -0.1558   0.02341   0.01474  -0.0637   1.0000   0.0565
  -2.750  -0.1296   0.02243   0.01343  -0.0632   1.0000   0.0597
  -2.500  -0.1037   0.02108   0.01215  -0.0633   1.0000   0.0668
  -2.250  -0.0773   0.02012   0.01112  -0.0631   1.0000   0.0742
  -2.000  -0.0490   0.01905   0.01023  -0.0634   1.0000   0.1035
  -1.750  -0.0164   0.01696   0.00994  -0.0652   1.0000   0.4502
  -1.500   0.0028   0.01655   0.01027  -0.0633   1.0000   0.6568
  -1.250   0.0097   0.01622   0.01047  -0.0582   1.0000   0.8454
  -1.000   0.0466   0.01636   0.01038  -0.0609   0.9930   1.0000
  -0.750   0.0923   0.01698   0.01060  -0.0651   0.9853   1.0000
  -0.500   0.1338   0.01743   0.01077  -0.0685   0.9761   1.0000
  -0.250   0.1752   0.01789   0.01099  -0.0718   0.9673   1.0000
   0.000   0.2204   0.01835   0.01125  -0.0756   0.9596   1.0000
   0.250   0.2573   0.01865   0.01140  -0.0779   0.9491   1.0000
   0.500   0.2961   0.01895   0.01158  -0.0804   0.9393   1.0000
   0.750   0.3433   0.01923   0.01175  -0.0844   0.9319   1.0000
   1.000   0.3785   0.01941   0.01186  -0.0860   0.9204   1.0000
   1.250   0.4154   0.01956   0.01197  -0.0880   0.9094   1.0000
   1.500   0.4566   0.01964   0.01203  -0.0905   0.8998   1.0000
   1.750   0.5010   0.01959   0.01198  -0.0934   0.8908   1.0000
   2.000   0.5372   0.01956   0.01197  -0.0948   0.8789   1.0000
   2.250   0.5760   0.01943   0.01189  -0.0965   0.8677   1.0000
   2.500   0.6308   0.01884   0.01137  -0.1007   0.8614   1.0000
   2.750   0.6683   0.01853   0.01114  -0.1018   0.8488   1.0000
   3.000   0.7063   0.01814   0.01086  -0.1029   0.8361   1.0000
   3.250   0.7449   0.01767   0.01049  -0.1039   0.8230   1.0000
   3.500   0.7832   0.01715   0.01007  -0.1046   0.8087   1.0000
   3.750   0.8208   0.01661   0.00966  -0.1052   0.7928   1.0000
   4.000   0.8576   0.01612   0.00925  -0.1055   0.7752   1.0000
   4.250   0.8857   0.01591   0.00913  -0.1046   0.7517   1.0000
   4.500   0.9155   0.01568   0.00896  -0.1038   0.7265   1.0000
   4.750   0.9433   0.01555   0.00890  -0.1027   0.6976   1.0000
   5.000   0.9695   0.01553   0.00889  -0.1014   0.6646   1.0000
   5.250   0.9936   0.01564   0.00898  -0.0998   0.6273   1.0000
   5.500   1.0159   0.01588   0.00918  -0.0980   0.5852   1.0000
   5.750   1.0361   0.01625   0.00945  -0.0959   0.5374   1.0000
   6.000   1.0542   0.01678   0.00982  -0.0935   0.4842   1.0000
   6.250   1.0702   0.01750   0.01032  -0.0911   0.4264   1.0000
   6.500   1.0835   0.01841   0.01093  -0.0883   0.3620   1.0000
   6.750   1.0947   0.01950   0.01168  -0.0855   0.2932   1.0000
   7.000   1.1057   0.02077   0.01255  -0.0830   0.2277   1.0000
   7.250   1.1168   0.02224   0.01368  -0.0806   0.1668   1.0000
   7.500   1.1219   0.02460   0.01549  -0.0773   0.1011   1.0000
   7.750   1.1287   0.02696   0.01755  -0.0740   0.0707   1.0000
   8.000   1.1423   0.02899   0.01957  -0.0717   0.0605   1.0000
   8.250   1.1618   0.03144   0.02197  -0.0703   0.0551   1.0000
   8.500   1.1876   0.03370   0.02443  -0.0697   0.0513   1.0000
   8.750   1.2112   0.03598   0.02675  -0.0692   0.0476   1.0000
   9.000   1.2370   0.03945   0.03039  -0.0690   0.0449   1.0000
   9.250   1.2571   0.04240   0.03378  -0.0677   0.0439   1.0000
   9.500   1.2729   0.04585   0.03768  -0.0659   0.0436   1.0000
   9.750   1.2832   0.04961   0.04191  -0.0637   0.0436   1.0000
  10.000   1.2886   0.05365   0.04639  -0.0612   0.0440   1.0000
  10.250   1.2897   0.05796   0.05111  -0.0586   0.0444   1.0000
  10.500   1.2875   0.06266   0.05619  -0.0560   0.0450   1.0000
  10.750   1.2881   0.06818   0.06198  -0.0543   0.0458   1.0000
  11.000   1.2745   0.06980   0.06403  -0.0498   0.0469   1.0000
  11.250   1.2366   0.07328   0.06798  -0.0448   0.0480   1.0000
  11.500   1.2007   0.07829   0.07332  -0.0427   0.0491   1.0000
  11.750   1.1686   0.08411   0.07941  -0.0429   0.0499   1.0000
  12.000   1.1375   0.09084   0.08635  -0.0452   0.0505   1.0000
  12.250   1.1058   0.09893   0.09461  -0.0498   0.0512   1.0000
  12.500   1.0723   0.10922   0.10501  -0.0569   0.0520   1.0000
  12.750   1.0411   0.12193   0.11776  -0.0659   0.0536   1.0000
  13.000   1.0306   0.13055   0.12636  -0.0703   0.0554   1.0000
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