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EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 326 AIRFOIL (e326-il)
Reynolds number: 50,000
Max Cl/Cd: 17.7 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e326-il-50000.txt
Download as CSV file: xf-e326-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 326 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5291   0.14840   0.14157   0.0075   1.0000   0.1791
 -11.750  -0.4915   0.14107   0.13421   0.0102   1.0000   0.1889
 -11.500  -0.5155   0.14037   0.13363   0.0065   1.0000   0.1944
 -11.250  -0.4841   0.13411   0.12734   0.0086   1.0000   0.2047
 -11.000  -0.5004   0.13191   0.12527   0.0059   1.0000   0.2111
 -10.750  -0.4825   0.12766   0.12100   0.0068   1.0000   0.2230
 -10.500  -0.4731   0.12355   0.11694   0.0068   1.0000   0.2320
 -10.250  -0.5022   0.12248   0.11601   0.0038   1.0000   0.2412
 -10.000  -0.4897   0.11829   0.11186   0.0047   1.0000   0.2563
  -9.750  -0.4795   0.11445   0.10806   0.0054   1.0000   0.2712
  -9.500  -0.4806   0.11133   0.10502   0.0055   1.0000   0.2871
  -9.250  -0.4656   0.10713   0.10086   0.0068   1.0000   0.3051
  -9.000  -0.4457   0.10347   0.09723   0.0084   1.0000   0.3270
  -8.750  -0.4664   0.10182   0.09571   0.0089   1.0000   0.3500
  -8.500  -0.4295   0.09755   0.09142   0.0119   1.0000   0.3850
  -8.250  -0.4262   0.09559   0.08953   0.0148   1.0000   0.4255
  -8.000  -0.3940   0.09165   0.08561   0.0170   1.0000   0.4641
  -6.750  -0.4405   0.07257   0.06711   0.0133   1.0000   0.4450
  -6.500  -0.5050   0.06663   0.06141   0.0097   1.0000   0.3995
  -6.250  -0.5686   0.06089   0.05559   0.0064   1.0000   0.3374
  -6.000  -0.5780   0.05301   0.04607   0.0015   1.0000   0.1577
  -5.750  -0.5705   0.04957   0.04199   0.0049   1.0000   0.1295
  -5.500  -0.5649   0.04719   0.03905   0.0089   1.0000   0.1165
  -5.250  -0.5579   0.04448   0.03629   0.0118   1.0000   0.1138
  -5.000  -0.5561   0.04258   0.03422   0.0155   1.0000   0.1109
  -4.750  -0.5561   0.04102   0.03237   0.0195   1.0000   0.1078
  -4.500  -0.5538   0.03968   0.03062   0.0232   1.0000   0.1051
  -4.250  -0.0371   0.02625   0.01851  -0.0320   1.0000   1.0000
  -4.000  -0.0189   0.02573   0.01775  -0.0317   1.0000   1.0000
  -3.750  -0.0011   0.02532   0.01718  -0.0316   1.0000   1.0000
  -3.500   0.0155   0.02507   0.01681  -0.0314   1.0000   1.0000
  -3.250   0.0251   0.02522   0.01696  -0.0306   1.0000   1.0000
  -3.000   0.0030   0.02674   0.01858  -0.0262   1.0000   1.0000
  -2.750   0.0623   0.02652   0.01804  -0.0354   0.9698   1.0000
  -2.500   0.1442   0.02554   0.01666  -0.0472   0.9379   1.0000
  -2.250   0.2090   0.02481   0.01559  -0.0551   0.9059   1.0000
  -2.000   0.2488   0.02461   0.01510  -0.0578   0.8751   1.0000
  -1.750   0.2746   0.02472   0.01497  -0.0576   0.8482   1.0000
  -1.500   0.2952   0.02499   0.01505  -0.0567   0.8243   1.0000
  -1.250   0.3149   0.02526   0.01515  -0.0554   0.8043   1.0000
  -1.000   0.3340   0.02560   0.01536  -0.0542   0.7851   1.0000
  -0.750   0.3535   0.02597   0.01563  -0.0531   0.7681   1.0000
  -0.500   0.3728   0.02637   0.01593  -0.0520   0.7522   1.0000
  -0.250   0.3930   0.02678   0.01624  -0.0510   0.7375   1.0000
   0.000   0.4129   0.02720   0.01657  -0.0499   0.7242   1.0000
   0.250   0.4324   0.02768   0.01699  -0.0489   0.7110   1.0000
   0.500   0.4519   0.02825   0.01754  -0.0481   0.6979   1.0000
   0.750   0.4713   0.02888   0.01815  -0.0474   0.6859   1.0000
   1.000   0.4906   0.02945   0.01868  -0.0463   0.6752   1.0000
   1.250   0.5099   0.03003   0.01923  -0.0452   0.6645   1.0000
   1.500   0.5285   0.03091   0.02016  -0.0447   0.6533   1.0000
   1.750   0.5474   0.03161   0.02084  -0.0437   0.6439   1.0000
   2.000   0.5658   0.03238   0.02163  -0.0427   0.6338   1.0000
   2.250   0.5828   0.03349   0.02280  -0.0421   0.6238   1.0000
   2.500   0.6023   0.03403   0.02333  -0.0406   0.6160   1.0000
   2.750   0.6164   0.03550   0.02493  -0.0402   0.6053   1.0000
   3.000   0.6333   0.03648   0.02593  -0.0390   0.5972   1.0000
   3.250   0.6471   0.03784   0.02738  -0.0382   0.5880   1.0000
   3.500   0.6593   0.03935   0.02896  -0.0371   0.5794   1.0000
   3.750   0.6737   0.04052   0.03019  -0.0357   0.5712   1.0000
   4.000   0.6792   0.04268   0.03248  -0.0346   0.5626   1.0000
   4.250   0.6940   0.04374   0.03358  -0.0329   0.5549   1.0000
   4.500   0.6887   0.04674   0.03670  -0.0314   0.5467   1.0000
   4.750   0.7022   0.04791   0.03792  -0.0296   0.5394   1.0000
   5.000   0.6855   0.05155   0.04163  -0.0274   0.5321   1.0000
   5.250   0.6817   0.05396   0.04410  -0.0251   0.5253   1.0000
   5.500   0.6762   0.05648   0.04665  -0.0226   0.5193   1.0000
   5.750   0.6260   0.06123   0.05135  -0.0180   0.5158   1.0000
   6.000   0.5812   0.06465   0.05469  -0.0124   0.5151   1.0000
   6.250   0.5509   0.06762   0.05761  -0.0083   0.5148   1.0000
   6.500   0.5284   0.07040   0.06036  -0.0050   0.5151   1.0000
   6.750   0.5123   0.07322   0.06316  -0.0026   0.5175   1.0000
   7.000   0.5093   0.07616   0.06613  -0.0015   0.5228   1.0000
   9.500   0.4578   0.10230   0.09238   0.0079   0.5249   1.0000
   9.750   0.4590   0.10443   0.09455   0.0087   0.5130   1.0000
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