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EPPLER 593 AIRFOIL (e593-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 593 AIRFOIL (e593-il)
Reynolds number: 100,000
Max Cl/Cd: 36.31 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e593-il-100000-n5.txt
Download as CSV file: xf-e593-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 593 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3539   0.09635   0.09055  -0.0004   0.5638   0.0229
  -8.000  -0.3525   0.09234   0.08655  -0.0027   0.5619   0.0232
  -7.750  -0.3481   0.08895   0.08318  -0.0045   0.5596   0.0229
  -7.500  -0.3465   0.08515   0.07942  -0.0068   0.5572   0.0228
  -7.250  -0.3490   0.08119   0.07551  -0.0095   0.5553   0.0231
  -7.000  -0.3459   0.07691   0.07125  -0.0132   0.5532   0.0231
  -6.750  -0.3404   0.07230   0.06662  -0.0174   0.5513   0.0231
  -6.500  -0.3333   0.06675   0.06101  -0.0224   0.5495   0.0232
  -6.250  -0.3234   0.06082   0.05496  -0.0273   0.5478   0.0232
  -6.000  -0.3113   0.05397   0.04789  -0.0321   0.5463   0.0232
  -5.750  -0.2989   0.04478   0.03824  -0.0368   0.5450   0.0231
  -5.500  -0.2841   0.03603   0.02859  -0.0398   0.5432   0.0233
  -5.250  -0.2631   0.03131   0.02309  -0.0403   0.5405   0.0242
  -5.000  -0.2385   0.02958   0.02108  -0.0404   0.5374   0.0254
  -4.750  -0.2131   0.02722   0.01809  -0.0401   0.5347   0.0286
  -4.500  -0.1871   0.02647   0.01721  -0.0400   0.5322   0.0318
  -4.250  -0.1607   0.02494   0.01530  -0.0397   0.5302   0.0356
  -4.000  -0.1335   0.02407   0.01419  -0.0395   0.5279   0.0418
  -3.750  -0.1060   0.02339   0.01337  -0.0394   0.5252   0.0494
  -3.500  -0.0784   0.02290   0.01273  -0.0392   0.5223   0.0583
  -3.250  -0.0512   0.02245   0.01223  -0.0391   0.5196   0.0676
  -3.000  -0.0239   0.02201   0.01170  -0.0388   0.5172   0.0771
  -2.750   0.0034   0.02159   0.01116  -0.0386   0.5151   0.0872
  -2.500   0.0307   0.02124   0.01067  -0.0383   0.5132   0.0983
  -2.250   0.0586   0.02098   0.01037  -0.0382   0.5108   0.1102
  -2.000   0.0861   0.02074   0.01013  -0.0381   0.5083   0.1227
  -1.750   0.1135   0.02051   0.00992  -0.0380   0.5058   0.1359
  -1.500   0.1406   0.02030   0.00970  -0.0378   0.5034   0.1506
  -1.250   0.1678   0.02011   0.00948  -0.0375   0.5012   0.1673
  -1.000   0.1949   0.01996   0.00930  -0.0372   0.4993   0.1879
  -0.750   0.2220   0.01981   0.00917  -0.0370   0.4976   0.2127
  -0.500   0.2496   0.01975   0.00925  -0.0371   0.4953   0.2494
  -0.250   0.2771   0.01961   0.00936  -0.0372   0.4929   0.3122
   0.000   0.3305   0.01782   0.00944  -0.0416   0.4900   1.0000
   0.250   0.3570   0.01808   0.00949  -0.0413   0.4876   1.0000
   0.500   0.3835   0.01833   0.00955  -0.0410   0.4855   1.0000
   0.750   0.4100   0.01858   0.00962  -0.0406   0.4837   1.0000
   1.000   0.4364   0.01885   0.00972  -0.0403   0.4822   1.0000
   1.250   0.4629   0.01924   0.01002  -0.0401   0.4803   1.0000
   1.500   0.4892   0.01971   0.01048  -0.0402   0.4774   1.0000
   1.750   0.5155   0.02013   0.01086  -0.0401   0.4746   1.0000
   2.000   0.5417   0.02050   0.01118  -0.0399   0.4721   1.0000
   2.250   0.5680   0.02085   0.01147  -0.0397   0.4700   1.0000
   2.500   0.5943   0.02121   0.01175  -0.0395   0.4683   1.0000
   2.750   0.6206   0.02152   0.01199  -0.0392   0.4667   1.0000
   3.000   0.6468   0.02192   0.01233  -0.0390   0.4648   1.0000
   3.250   0.6716   0.02269   0.01323  -0.0392   0.4610   1.0000
   3.500   0.6969   0.02329   0.01388  -0.0393   0.4581   1.0000
   3.750   0.7224   0.02378   0.01437  -0.0391   0.4556   1.0000
   4.000   0.7482   0.02414   0.01472  -0.0389   0.4533   1.0000
   4.250   0.7743   0.02445   0.01501  -0.0386   0.4515   1.0000
   4.500   0.8006   0.02473   0.01525  -0.0382   0.4500   1.0000
   4.750   0.8225   0.02594   0.01667  -0.0386   0.4451   1.0000
   5.000   0.8463   0.02665   0.01745  -0.0386   0.4414   1.0000
   5.250   0.8713   0.02709   0.01795  -0.0383   0.4387   1.0000
   5.500   0.8972   0.02732   0.01818  -0.0379   0.4365   1.0000
   5.750   0.9238   0.02744   0.01829  -0.0375   0.4348   1.0000
   6.000   0.9418   0.02901   0.02013  -0.0379   0.4285   1.0000
   6.250   0.9650   0.02960   0.02081  -0.0377   0.4246   1.0000
   6.500   0.9907   0.02974   0.02098  -0.0372   0.4220   1.0000
   6.750   1.0179   0.02964   0.02090  -0.0366   0.4200   1.0000
   7.000   1.0325   0.03141   0.02293  -0.0369   0.4129   1.0000
   7.250   1.0557   0.03180   0.02341  -0.0365   0.4089   1.0000
   7.500   1.0831   0.03155   0.02321  -0.0358   0.4063   1.0000
   7.750   1.1126   0.03102   0.02269  -0.0351   0.4044   1.0000
   8.000   1.1189   0.03347   0.02545  -0.0353   0.3947   1.0000
   8.250   1.1476   0.03290   0.02494  -0.0345   0.3919   1.0000
   8.750   1.1813   0.03456   0.02693  -0.0337   0.3793   1.0000
   9.000   1.2139   0.03343   0.02585  -0.0328   0.3765   1.0000
   9.250   1.2112   0.03623   0.02891  -0.0327   0.3661   1.0000
   9.500   1.2451   0.03486   0.02762  -0.0317   0.3628   1.0000
   9.750   1.2313   0.03855   0.03151  -0.0317   0.3514   1.0000
  10.000   1.2433   0.03926   0.03231  -0.0310   0.3448   1.0000
  10.250   1.2311   0.04277   0.03589  -0.0316   0.3347   1.0000
  10.500   1.2081   0.04798   0.04114  -0.0328   0.3216   1.0000
  11.000   1.2027   0.05355   0.04683  -0.0332   0.3004   1.0000
  11.250   1.2273   0.05287   0.04625  -0.0322   0.2930   1.0000
  11.500   1.2247   0.05571   0.04915  -0.0324   0.2815   1.0000
  11.750   1.2342   0.05701   0.05050  -0.0321   0.2711   1.0000
  12.000   1.2547   0.05681   0.05034  -0.0312   0.2610   1.0000
  12.250   1.2732   0.05683   0.05036  -0.0304   0.2496   1.0000
  12.500   1.2774   0.05875   0.05227  -0.0302   0.2369   1.0000
  12.750   1.2788   0.06106   0.05458  -0.0301   0.2244   1.0000
  13.000   1.2796   0.06349   0.05700  -0.0302   0.2123   1.0000
  13.250   1.2799   0.06601   0.05951  -0.0302   0.2006   1.0000
  13.500   1.2805   0.06856   0.06203  -0.0304   0.1894   1.0000
  13.750   1.2813   0.07120   0.06463  -0.0306   0.1786   1.0000
  14.000   1.2791   0.07445   0.06791  -0.0313   0.1680   1.0000
  14.250   1.2766   0.07789   0.07139  -0.0320   0.1580   1.0000
  14.500   1.2758   0.08108   0.07457  -0.0327   0.1487   1.0000
  14.750   1.2747   0.08434   0.07781  -0.0334   0.1398   1.0000
  15.000   1.2718   0.08813   0.08168  -0.0345   0.1312   1.0000
  15.250   1.2705   0.09159   0.08514  -0.0354   0.1233   1.0000
  15.500   1.2678   0.09541   0.08900  -0.0366   0.1157   1.0000
  15.750   1.2660   0.09916   0.09281  -0.0377   0.1086   1.0000
  16.000   1.2639   0.10296   0.09661  -0.0390   0.1021   1.0000
  16.250   1.2616   0.10695   0.10071  -0.0404   0.0957   1.0000
  16.500   1.2592   0.11092   0.10468  -0.0418   0.0899   1.0000
  16.750   1.2571   0.11498   0.10885  -0.0433   0.0844   1.0000
  17.000   1.2544   0.11916   0.11307  -0.0450   0.0793   1.0000
  17.250   1.2528   0.12317   0.11714  -0.0466   0.0746   1.0000
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