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EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 67 AIRFOIL (e67-il)
Reynolds number: 100,000
Max Cl/Cd: 60.87 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e67-il-100000.txt
Download as CSV file: xf-e67-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 67 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4139   0.10288   0.09842  -0.0349   1.0000   0.1173
  -8.250  -0.4513   0.10194   0.09764  -0.0348   1.0000   0.1183
  -8.000  -0.4870   0.10082   0.09667  -0.0337   1.0000   0.1185
  -7.750  -0.4439   0.09531   0.09109  -0.0298   1.0000   0.1214
  -7.500  -0.4450   0.09332   0.08914  -0.0271   1.0000   0.1244
  -7.250  -0.4610   0.09169   0.08759  -0.0247   1.0000   0.1273
  -7.000  -0.4817   0.08977   0.08576  -0.0229   1.0000   0.1284
  -6.750  -0.5328   0.08359   0.07960  -0.0366   1.0000   0.1331
  -6.500  -0.5218   0.08116   0.07727  -0.0305   1.0000   0.1344
  -6.250  -0.5393   0.05298   0.04790  -0.0517   1.0000   0.0632
  -6.000  -0.5275   0.04822   0.04295  -0.0528   1.0000   0.0610
  -5.750  -0.5101   0.04285   0.03706  -0.0549   1.0000   0.0597
  -5.500  -0.4885   0.03866   0.03224  -0.0565   1.0000   0.0608
  -5.250  -0.4645   0.03515   0.02807  -0.0575   1.0000   0.0618
  -5.000  -0.4392   0.03222   0.02453  -0.0580   1.0000   0.0627
  -4.750  -0.4137   0.02998   0.02172  -0.0581   1.0000   0.0646
  -4.500  -0.3776   0.02799   0.01964  -0.0605   0.9964   0.0705
  -4.250  -0.3383   0.02685   0.01831  -0.0631   0.9915   0.0835
  -4.000  -0.2992   0.02595   0.01717  -0.0655   0.9864   0.1045
  -3.750  -0.2611   0.02513   0.01646  -0.0681   0.9814   0.1342
  -3.500  -0.2261   0.02452   0.01601  -0.0702   0.9755   0.1680
  -3.250  -0.1858   0.02413   0.01575  -0.0731   0.9708   0.2141
  -3.000  -0.1549   0.02365   0.01546  -0.0743   0.9637   0.2655
  -2.750  -0.1154   0.02343   0.01553  -0.0771   0.9589   0.3364
  -2.500  -0.0871   0.02316   0.01554  -0.0777   0.9513   0.4048
  -2.250  -0.0494   0.02315   0.01582  -0.0798   0.9460   0.4882
  -2.000  -0.0239   0.02310   0.01599  -0.0795   0.9379   0.5569
  -1.750   0.0111   0.02322   0.01632  -0.0805   0.9324   0.6309
  -1.500   0.0326   0.02327   0.01650  -0.0791   0.9237   0.6904
  -1.250   0.0648   0.02342   0.01676  -0.0791   0.9182   0.7558
  -1.000   0.0803   0.02345   0.01689  -0.0763   0.9088   0.8125
  -0.750   0.1082   0.02342   0.01695  -0.0750   0.9034   0.8861
  -0.500   0.1453   0.02326   0.01675  -0.0774   0.8938   1.0000
  -0.250   0.1957   0.02348   0.01671  -0.0825   0.8892   1.0000
   0.000   0.2224   0.02375   0.01680  -0.0833   0.8791   1.0000
   0.250   0.2702   0.02391   0.01679  -0.0872   0.8748   1.0000
   0.500   0.2939   0.02422   0.01698  -0.0872   0.8642   1.0000
   0.750   0.3297   0.02443   0.01708  -0.0890   0.8570   1.0000
   1.000   0.3642   0.02460   0.01716  -0.0905   0.8491   1.0000
   1.250   0.3943   0.02485   0.01733  -0.0913   0.8403   1.0000
   1.500   0.4352   0.02483   0.01726  -0.0935   0.8340   1.0000
   1.750   0.4619   0.02510   0.01748  -0.0936   0.8241   1.0000
   2.000   0.5068   0.02487   0.01723  -0.0963   0.8190   1.0000
   2.250   0.5321   0.02513   0.01748  -0.0961   0.8084   1.0000
   2.500   0.5805   0.02465   0.01700  -0.0991   0.8043   1.0000
   2.750   0.6048   0.02488   0.01723  -0.0985   0.7931   1.0000
   3.000   0.6574   0.02408   0.01648  -0.1020   0.7899   1.0000
   3.250   0.6820   0.02422   0.01665  -0.1013   0.7785   1.0000
   3.500   0.7386   0.02325   0.01576  -0.1053   0.7752   1.0000
   3.750   0.7654   0.02321   0.01578  -0.1048   0.7636   1.0000
   4.000   0.8002   0.02287   0.01550  -0.1054   0.7539   1.0000
   4.250   0.8503   0.02191   0.01461  -0.1081   0.7474   1.0000
   4.500   0.8814   0.02162   0.01443  -0.1080   0.7353   1.0000
   4.750   0.9163   0.02119   0.01408  -0.1084   0.7234   1.0000
   5.000   0.9537   0.02065   0.01361  -0.1092   0.7109   1.0000
   5.250   0.9889   0.02019   0.01325  -0.1095   0.6967   1.0000
   5.500   1.0215   0.01982   0.01295  -0.1095   0.6807   1.0000
   5.750   1.0539   0.01947   0.01265  -0.1094   0.6631   1.0000
   6.000   1.0871   0.01915   0.01237  -0.1095   0.6443   1.0000
   6.250   1.1081   0.01919   0.01249  -0.1076   0.6217   1.0000
   6.500   1.1340   0.01912   0.01243  -0.1065   0.5982   1.0000
   6.750   1.1579   0.01914   0.01243  -0.1051   0.5723   1.0000
   7.000   1.1766   0.01933   0.01261  -0.1029   0.5436   1.0000
   7.250   1.1928   0.01962   0.01291  -0.1004   0.5123   1.0000
   7.500   1.2065   0.02001   0.01327  -0.0975   0.4782   1.0000
   7.750   1.2190   0.02052   0.01365  -0.0944   0.4422   1.0000
   8.000   1.2276   0.02118   0.01421  -0.0909   0.4039   1.0000
   8.250   1.2338   0.02199   0.01486  -0.0871   0.3649   1.0000
   8.500   1.2366   0.02295   0.01562  -0.0829   0.3275   1.0000
   8.750   1.2382   0.02407   0.01657  -0.0787   0.2897   1.0000
   9.000   1.2388   0.02540   0.01768  -0.0747   0.2549   1.0000
   9.250   1.2397   0.02685   0.01896  -0.0710   0.2212   1.0000
   9.500   1.2403   0.02844   0.02038  -0.0674   0.1908   1.0000
   9.750   1.2409   0.03018   0.02195  -0.0642   0.1638   1.0000
  10.000   1.2415   0.03207   0.02365  -0.0611   0.1408   1.0000
  10.250   1.2433   0.03399   0.02552  -0.0584   0.1195   1.0000
  10.500   1.2456   0.03617   0.02750  -0.0559   0.1026   1.0000
  10.750   1.2515   0.03836   0.02965  -0.0537   0.0880   1.0000
  11.000   1.2631   0.04065   0.03185  -0.0521   0.0763   1.0000
  11.250   1.2716   0.04260   0.03394  -0.0503   0.0678   1.0000
  11.500   1.2908   0.04505   0.03652  -0.0493   0.0607   1.0000
  11.750   1.3097   0.04734   0.03885  -0.0485   0.0556   1.0000
  12.000   1.3302   0.05044   0.04213  -0.0479   0.0511   1.0000
  12.250   1.3366   0.05291   0.04490  -0.0461   0.0480   1.0000
  12.500   1.3457   0.05581   0.04804  -0.0448   0.0459   1.0000
  12.750   1.3558   0.05908   0.05147  -0.0437   0.0442   1.0000
  13.000   1.3675   0.06472   0.05733  -0.0434   0.0425   1.0000
  13.250   1.3534   0.06805   0.06099  -0.0409   0.0421   1.0000
  13.500   1.3378   0.07168   0.06497  -0.0389   0.0418   1.0000
  13.750   1.3204   0.07579   0.06941  -0.0376   0.0416   1.0000
  14.000   1.3017   0.08038   0.07430  -0.0369   0.0414   1.0000
  14.250   1.2811   0.08543   0.07964  -0.0370   0.0413   1.0000
  14.500   1.2595   0.09100   0.08549  -0.0378   0.0413   1.0000
  14.750   1.2372   0.09711   0.09184  -0.0395   0.0414   1.0000
  15.000   1.2150   0.10374   0.09869  -0.0420   0.0417   1.0000
  15.250   1.1932   0.11092   0.10605  -0.0452   0.0420   1.0000
  15.500   1.1723   0.11862   0.11392  -0.0491   0.0423   1.0000
  15.750   1.0579   0.15030   0.14612  -0.0732   0.0510   1.0000
  16.000   1.0427   0.16105   0.15680  -0.0792   0.0523   1.0000
  16.250   1.0399   0.16807   0.16380  -0.0822   0.0531   1.0000
  16.500   1.0234   0.18616   0.18185  -0.0906   0.0650   1.0000
  16.750   0.7895   0.19812   0.19437  -0.0925   0.1150   1.0000
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