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EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 379 AIRFOIL (e379-il)
Reynolds number: 200,000
Max Cl/Cd: 91.16 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e379-il-200000-n5.txt
Download as CSV file: xf-e379-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 379 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4399   0.15112   0.14770   0.0258   1.0000   0.0055
 -12.000  -0.4312   0.14817   0.14476   0.0242   1.0000   0.0055
 -11.750  -0.4225   0.14518   0.14179   0.0227   1.0000   0.0055
 -11.500  -0.4135   0.14225   0.13887   0.0212   1.0000   0.0056
 -11.250  -0.4047   0.13932   0.13596   0.0197   1.0000   0.0055
 -11.000  -0.3959   0.13643   0.13309   0.0182   1.0000   0.0054
 -10.750  -0.3868   0.13354   0.13022   0.0167   1.0000   0.0055
 -10.500  -0.3778   0.13071   0.12741   0.0153   1.0000   0.0055
 -10.250  -0.3688   0.12787   0.12459   0.0138   1.0000   0.0056
 -10.000  -0.3596   0.12510   0.12184   0.0124   1.0000   0.0056
  -9.750  -0.3503   0.12232   0.11909   0.0109   1.0000   0.0056
  -9.500  -0.3411   0.11960   0.11640   0.0095   1.0000   0.0057
  -9.250  -0.3317   0.11689   0.11368   0.0081   1.0000   0.0058
  -9.000  -0.3223   0.11424   0.11105   0.0067   1.0000   0.0057
  -8.750  -0.3127   0.11162   0.10847   0.0053   1.0000   0.0059
  -8.500  -0.3031   0.10903   0.10593   0.0039   1.0000   0.0060
  -8.250  -0.2938   0.10648   0.10342   0.0025   1.0000   0.0060
  -8.000  -0.2836   0.10401   0.10098   0.0009   0.9608   0.0061
  -7.750  -0.2612   0.10069   0.09753  -0.0038   0.8803   0.0063
  -7.500  -0.2522   0.09840   0.09513  -0.0047   0.8377   0.0062
  -7.000  -0.2311   0.09426   0.09080  -0.0071   0.7819   0.0065
  -6.750  -0.2187   0.09189   0.08834  -0.0088   0.7606   0.0066
  -6.500  -0.2034   0.08983   0.08619  -0.0111   0.7430   0.0067
  -6.250  -0.1870   0.08766   0.08394  -0.0136   0.7268   0.0068
  -6.000  -0.1697   0.08535   0.08156  -0.0162   0.7128   0.0069
  -5.750  -0.1501   0.08319   0.07932  -0.0193   0.6997   0.0069
  -5.500  -0.1307   0.08068   0.07669  -0.0222   0.6879   0.0070
  -5.250  -0.1076   0.07847   0.07440  -0.0258   0.6773   0.0070
  -5.000  -0.0838   0.07612   0.07197  -0.0294   0.6671   0.0071
  -4.750  -0.0590   0.07368   0.06946  -0.0329   0.6576   0.0071
  -4.500  -0.0328   0.07119   0.06689  -0.0366   0.6485   0.0071
  -2.500   0.1827   0.04678   0.04190  -0.0606   0.5927   0.0086
  -2.250   0.2139   0.04441   0.03941  -0.0635   0.5872   0.0102
  -2.000   0.2482   0.04207   0.03699  -0.0667   0.5810   0.0110
  -1.750   0.2824   0.03992   0.03470  -0.0696   0.5756   0.0121
  -1.500   0.3172   0.03792   0.03259  -0.0722   0.5700   0.0132
  -1.250   0.3526   0.03613   0.03062  -0.0747   0.5645   0.0140
  -1.000   0.3881   0.03452   0.02884  -0.0769   0.5596   0.0142
  -0.750   0.4235   0.03293   0.02713  -0.0789   0.5540   0.0144
  -0.500   0.4581   0.03141   0.02544  -0.0805   0.5491   0.0145
  -0.250   0.4919   0.02990   0.02378  -0.0819   0.5444   0.0145
   0.000   0.5249   0.02837   0.02210  -0.0831   0.5391   0.0146
   0.250   0.5570   0.02688   0.02043  -0.0839   0.5346   0.0146
   0.500   0.5886   0.02539   0.01879  -0.0847   0.5300   0.0146
   0.750   0.6194   0.02391   0.01717  -0.0853   0.5251   0.0146
   1.000   0.6471   0.02218   0.01528  -0.0860   0.5209   0.0131
   1.250   0.6785   0.02087   0.01373  -0.0863   0.5162   0.0102
   1.500   0.7102   0.01964   0.01230  -0.0864   0.5115   0.0090
   1.750   0.7414   0.01842   0.01081  -0.0862   0.5076   0.0083
   2.000   0.7721   0.01717   0.00931  -0.0860   0.5032   0.0079
   2.250   0.8019   0.01600   0.00791  -0.0857   0.4985   0.0079
   2.500   0.8306   0.01502   0.00665  -0.0854   0.4945   0.0084
   3.000   0.8857   0.01391   0.00519  -0.0848   0.4853   0.0235
   3.250   0.9126   0.01354   0.00470  -0.0846   0.4810   0.0331
   3.500   0.9395   0.01332   0.00441  -0.0843   0.4766   0.0324
   3.750   0.9666   0.01328   0.00435  -0.0841   0.4713   0.0324
   4.000   0.9935   0.01332   0.00429  -0.0839   0.4669   0.0333
   4.250   1.0204   0.01340   0.00434  -0.0838   0.4620   0.0361
   4.500   1.0472   0.01346   0.00449  -0.0836   0.4565   0.0813
   4.750   1.0737   0.01357   0.00464  -0.0834   0.4519   0.1672
   5.000   1.1091   0.01280   0.00491  -0.0855   0.4447   1.0000
   5.250   1.1350   0.01298   0.00512  -0.0852   0.4387   1.0000
   5.500   1.1612   0.01314   0.00533  -0.0850   0.4309   1.0000
   5.750   1.1870   0.01333   0.00549  -0.0847   0.4243   1.0000
   6.000   1.2129   0.01351   0.00574  -0.0845   0.4161   1.0000
   6.250   1.2386   0.01371   0.00597  -0.0842   0.4084   1.0000
   6.500   1.2643   0.01390   0.00622  -0.0840   0.3998   1.0000
   6.750   1.2872   0.01412   0.00614  -0.0835   0.3380   1.0000
   7.000   1.2837   0.01959   0.00919  -0.0827   0.0176   1.0000
   7.250   1.3053   0.02036   0.01020  -0.0821   0.0055   1.0000
   7.500   1.3271   0.02108   0.01103  -0.0815   0.0040   1.0000
   7.750   1.3485   0.02185   0.01202  -0.0808   0.0032   1.0000
   8.000   1.3687   0.02274   0.01315  -0.0800   0.0029   1.0000
   8.250   1.3876   0.02377   0.01442  -0.0791   0.0027   1.0000
   8.500   1.4044   0.02500   0.01593  -0.0780   0.0026   1.0000
   8.750   1.4189   0.02640   0.01759  -0.0768   0.0026   1.0000
   9.000   1.4305   0.02799   0.01944  -0.0753   0.0025   1.0000
   9.250   1.4381   0.02981   0.02150  -0.0737   0.0025   1.0000
   9.500   1.4409   0.03178   0.02368  -0.0717   0.0025   1.0000
   9.750   1.4375   0.03404   0.02612  -0.0696   0.0026   1.0000
  10.000   1.4339   0.03675   0.02900  -0.0683   0.0026   1.0000
  10.250   1.4301   0.03982   0.03223  -0.0676   0.0026   1.0000
  10.500   1.4278   0.04291   0.03548  -0.0671   0.0026   1.0000
  10.750   1.4245   0.04624   0.03896  -0.0667   0.0026   1.0000
  11.000   1.4227   0.04946   0.04232  -0.0662   0.0027   1.0000
  11.250   1.4211   0.05272   0.04574  -0.0656   0.0027   1.0000
  11.500   1.4201   0.05598   0.04915  -0.0648   0.0028   1.0000
  11.750   1.4205   0.05922   0.05275  -0.0641   0.0029   1.0000
  12.000   1.4205   0.06259   0.05632  -0.0633   0.0029   1.0000
  12.250   1.4200   0.06616   0.06011  -0.0627   0.0030   1.0000
  12.500   1.4181   0.07006   0.06425  -0.0624   0.0031   1.0000
  12.750   1.4141   0.07438   0.06882  -0.0624   0.0032   1.0000
  13.000   1.4082   0.07906   0.07374  -0.0630   0.0032   1.0000
  13.250   1.4002   0.08416   0.07908  -0.0639   0.0033   1.0000
  13.500   1.3904   0.08963   0.08478  -0.0654   0.0034   1.0000
  13.750   1.3793   0.09555   0.09094  -0.0675   0.0034   1.0000
  14.000   1.3676   0.10181   0.09742  -0.0700   0.0035   1.0000
  14.250   1.3552   0.10848   0.10431  -0.0730   0.0035   1.0000
  14.500   1.3427   0.11547   0.11150  -0.0765   0.0036   1.0000
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