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EPPLER 378 AIRFOIL (e378-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 378 AIRFOIL (e378-il)
Reynolds number: 500,000
Max Cl/Cd: 124.67 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e378-il-500000-n5.txt
Download as CSV file: xf-e378-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 378 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2403   0.10017   0.09690  -0.0066   0.6541   0.0056
  -7.250  -0.2320   0.09776   0.09449  -0.0075   0.6466   0.0056
  -7.000  -0.2226   0.09542   0.09212  -0.0087   0.6381   0.0056
  -6.750  -0.2105   0.09281   0.08947  -0.0106   0.6286   0.0056
  -6.500  -0.1968   0.09013   0.08678  -0.0130   0.6223   0.0056
  -6.250  -0.1830   0.08745   0.08407  -0.0149   0.6138   0.0056
  -6.000  -0.1703   0.08390   0.08050  -0.0167   0.6073   0.0057
  -5.750  -0.1547   0.08106   0.07764  -0.0190   0.6007   0.0058
  -5.500  -0.1388   0.07835   0.07491  -0.0211   0.5942   0.0059
  -5.250  -0.1204   0.07571   0.07223  -0.0239   0.5876   0.0060
  -5.000  -0.1009   0.07305   0.06952  -0.0267   0.5820   0.0062
  -4.750  -0.0791   0.07031   0.06675  -0.0300   0.5760   0.0063
  -4.500  -0.0570   0.06760   0.06401  -0.0330   0.5702   0.0066
  -4.250  -0.0322   0.06482   0.06119  -0.0367   0.5649   0.0068
  -4.000  -0.0064   0.06199   0.05832  -0.0404   0.5596   0.0072
  -3.750   0.0215   0.05912   0.05539  -0.0442   0.5545   0.0079
  -3.500   0.0557   0.05617   0.05239  -0.0493   0.5492   0.0087
  -3.250   0.0907   0.05317   0.04931  -0.0544   0.5442   0.0088
  -3.000   0.1242   0.05014   0.04619  -0.0587   0.5397   0.0089
  -2.750   0.1586   0.04695   0.04294  -0.0630   0.5349   0.0089
  -2.500   0.1877   0.04392   0.03985  -0.0660   0.5301   0.0083
  -2.250   0.2204   0.04171   0.03756  -0.0694   0.5256   0.0106
  -2.000   0.2673   0.03953   0.03526  -0.0748   0.5210   0.0138
  -1.250   0.3790   0.02987   0.02522  -0.0855   0.5082   0.0086
  -1.000   0.4183   0.02698   0.02218  -0.0887   0.5039   0.0084
  -0.750   0.4620   0.02319   0.01814  -0.0924   0.5002   0.0085
  -0.500   0.5210   0.01221   0.00593  -0.0989   0.4972   0.0089
  -0.250   0.5463   0.01119   0.00461  -0.0980   0.4925   0.0103
   0.000   0.5737   0.01095   0.00428  -0.0978   0.4878   0.0121
   0.250   0.6010   0.01056   0.00373  -0.0973   0.4836   0.0130
   0.500   0.6281   0.01023   0.00331  -0.0968   0.4795   0.0146
   0.750   0.6549   0.00999   0.00302  -0.0962   0.4750   0.0208
   1.000   0.6816   0.00989   0.00289  -0.0957   0.4707   0.0310
   1.250   0.7085   0.00985   0.00287  -0.0954   0.4667   0.0431
   1.500   0.7357   0.00985   0.00285  -0.0951   0.4624   0.0516
   1.750   0.7626   0.00982   0.00279  -0.0947   0.4580   0.0581
   2.000   0.7895   0.00985   0.00277  -0.0943   0.4539   0.0648
   2.250   0.8166   0.00982   0.00276  -0.0940   0.4497   0.0717
   2.500   0.8436   0.00985   0.00275  -0.0937   0.4451   0.0783
   2.750   0.8775   0.00957   0.00218  -0.0951   0.4417   0.0876
   3.000   0.9047   0.00959   0.00221  -0.0949   0.4374   0.0947
   3.250   0.9319   0.00963   0.00227  -0.0947   0.4325   0.1035
   3.500   0.9589   0.00970   0.00235  -0.0944   0.4277   0.1140
   3.750   0.9860   0.00975   0.00243  -0.0942   0.4226   0.1238
   4.000   1.0130   0.00983   0.00253  -0.0940   0.4165   0.1339
   4.250   1.0398   0.00992   0.00264  -0.0937   0.4103   0.1458
   4.500   1.0667   0.01000   0.00275  -0.0935   0.4035   0.1602
   4.750   1.0935   0.01010   0.00289  -0.0933   0.3972   0.1745
   5.000   1.1203   0.01019   0.00303  -0.0931   0.3898   0.1919
   5.250   1.1469   0.01032   0.00322  -0.0929   0.3821   0.2117
   5.500   1.1734   0.01044   0.00339  -0.0927   0.3735   0.2325
   5.750   1.1999   0.01057   0.00358  -0.0925   0.3650   0.2612
   6.000   1.2261   0.01073   0.00379  -0.0922   0.3551   0.2968
   6.250   1.2510   0.01055   0.00408  -0.0919   0.3441   0.6991
   6.500   1.2866   0.01032   0.00432  -0.0938   0.3299   1.0000
   6.750   1.3122   0.01061   0.00457  -0.0935   0.3149   1.0000
   7.000   1.3374   0.01093   0.00487  -0.0931   0.2971   1.0000
   7.250   1.3537   0.01161   0.00521  -0.0910   0.2803   0.7851
   7.500   1.3879   0.01190   0.00571  -0.0930   0.2470   1.0000
   7.750   1.4112   0.01258   0.00625  -0.0926   0.2150   1.0000
   8.000   1.4331   0.01348   0.00695  -0.0922   0.1776   1.0000
   8.250   1.4552   0.01430   0.00764  -0.0917   0.1477   1.0000
   8.500   1.4774   0.01504   0.00829  -0.0913   0.1262   1.0000
   8.750   1.4991   0.01582   0.00902  -0.0908   0.1051   1.0000
   9.000   1.5193   0.01677   0.00985  -0.0902   0.0815   1.0000
   9.250   1.5389   0.01773   0.01071  -0.0895   0.0628   1.0000
   9.500   1.5588   0.01858   0.01153  -0.0888   0.0502   1.0000
   9.750   1.5777   0.01949   0.01242  -0.0881   0.0387   1.0000
  10.000   1.5956   0.02045   0.01336  -0.0872   0.0292   1.0000
  10.250   1.6127   0.02143   0.01434  -0.0863   0.0222   1.0000
  10.500   1.6288   0.02241   0.01540  -0.0852   0.0169   1.0000
  10.750   1.6419   0.02361   0.01662  -0.0839   0.0110   1.0000
  11.000   1.6495   0.02518   0.01819  -0.0822   0.0055   1.0000
  11.250   1.6556   0.02659   0.01968  -0.0802   0.0039   1.0000
  11.500   1.6551   0.02823   0.02142  -0.0778   0.0033   1.0000
  11.750   1.6551   0.03024   0.02356  -0.0763   0.0028   1.0000
  12.000   1.6560   0.03252   0.02598  -0.0755   0.0026   1.0000
  12.250   1.6558   0.03503   0.02862  -0.0747   0.0023   1.0000
  12.500   1.6565   0.03755   0.03126  -0.0741   0.0023   1.0000
  12.750   1.6535   0.04079   0.03464  -0.0741   0.0021   1.0000
  13.000   1.6504   0.04413   0.03811  -0.0742   0.0020   1.0000
  13.250   1.6442   0.04793   0.04205  -0.0744   0.0018   1.0000
  13.500   1.6373   0.05190   0.04618  -0.0746   0.0017   1.0000
  13.750   1.6271   0.05641   0.05084  -0.0752   0.0016   1.0000
  14.000   1.6186   0.06078   0.05536  -0.0759   0.0016   1.0000
  14.250   1.6126   0.06479   0.05949  -0.0763   0.0015   1.0000
  14.500   1.6070   0.06891   0.06375  -0.0771   0.0014   1.0000
  14.750   1.6008   0.07328   0.06825  -0.0781   0.0014   1.0000
  15.000   1.5930   0.07803   0.07313  -0.0792   0.0013   1.0000
  15.250   1.5852   0.08294   0.07816  -0.0805   0.0013   1.0000
  15.500   1.5789   0.08771   0.08306  -0.0820   0.0012   1.0000
  15.750   1.5696   0.09317   0.08866  -0.0838   0.0012   1.0000
  16.000   1.5632   0.09821   0.09382  -0.0854   0.0011   1.0000
  16.250   1.5525   0.10416   0.09991  -0.0876   0.0011   1.0000
  16.500   1.5437   0.10991   0.10579  -0.0898   0.0010   1.0000
  16.750   1.5348   0.11581   0.11182  -0.0922   0.0010   1.0000
  17.000   1.5253   0.12193   0.11807  -0.0949   0.0010   1.0000
  17.250   1.5151   0.12832   0.12460  -0.0978   0.0009   1.0000
  17.500   1.5054   0.13477   0.13117  -0.1008   0.0009   1.0000
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