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EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 67 AIRFOIL (e67-il)
Reynolds number: 50,000
Max Cl/Cd: 37.36 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e67-il-50000.txt
Download as CSV file: xf-e67-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3812   0.11176   0.10527  -0.0283   1.0000   0.2485
  -8.250  -0.3666   0.10768   0.10120  -0.0262   1.0000   0.2599
  -8.000  -0.3992   0.10806   0.10178  -0.0245   1.0000   0.2636
  -7.750  -0.3848   0.10406   0.09778  -0.0223   1.0000   0.2766
  -7.500  -0.3821   0.10092   0.09470  -0.0202   1.0000   0.2843
  -7.250  -0.4090   0.10078   0.09472  -0.0175   1.0000   0.2924
  -7.000  -0.3988   0.09690   0.09087  -0.0156   1.0000   0.2991
  -6.750  -0.4320   0.09718   0.09132  -0.0119   1.0000   0.3073
  -6.500  -0.4216   0.09319   0.08736  -0.0101   1.0000   0.3136
  -6.250  -0.4629   0.09378   0.08815  -0.0065   1.0000   0.3226
  -6.000  -0.5129   0.06706   0.06086  -0.0452   1.0000   0.1327
  -5.750  -0.5036   0.06290   0.05666  -0.0451   1.0000   0.1312
  -5.500  -0.4924   0.05784   0.05140  -0.0471   1.0000   0.1292
  -5.250  -0.4756   0.05202   0.04515  -0.0504   1.0000   0.1265
  -5.000  -0.4515   0.04590   0.03830  -0.0544   1.0000   0.1242
  -4.750  -0.4257   0.04174   0.03351  -0.0564   1.0000   0.1280
  -4.500  -0.4008   0.03875   0.03005  -0.0575   1.0000   0.1374
  -4.250  -0.3729   0.03590   0.02657  -0.0586   1.0000   0.1488
  -4.000  -0.3496   0.03419   0.02477  -0.0584   1.0000   0.1665
  -3.750  -0.3237   0.03255   0.02278  -0.0586   1.0000   0.1910
  -3.500  -0.3002   0.03126   0.02145  -0.0583   1.0000   0.2189
  -3.250  -0.2769   0.03012   0.02036  -0.0578   1.0000   0.2513
  -3.000  -0.2542   0.02928   0.01952  -0.0573   1.0000   0.2932
  -2.750  -0.2330   0.02860   0.01910  -0.0564   1.0000   0.3414
  -2.500  -0.2120   0.02806   0.01879  -0.0553   1.0000   0.4006
  -2.250  -0.1919   0.02770   0.01869  -0.0539   1.0000   0.4696
  -2.000  -0.1737   0.02748   0.01875  -0.0519   1.0000   0.5457
  -1.750  -0.1594   0.02736   0.01892  -0.0488   1.0000   0.6226
  -1.500  -0.1497   0.02728   0.01912  -0.0445   1.0000   0.7002
  -1.250  -0.1456   0.02712   0.01920  -0.0390   1.0000   0.7818
  -1.000  -0.1466   0.02661   0.01897  -0.0323   1.0000   0.8879
  -0.750  -0.1102   0.02607   0.01810  -0.0376   1.0000   1.0000
  -0.500  -0.0788   0.02663   0.01817  -0.0409   1.0000   1.0000
  -0.250  -0.0530   0.02727   0.01844  -0.0425   1.0000   1.0000
   0.000  -0.0294   0.02794   0.01882  -0.0435   1.0000   1.0000
   0.250  -0.0071   0.02866   0.01929  -0.0443   1.0000   1.0000
   0.500   0.0143   0.02943   0.01982  -0.0448   1.0000   1.0000
   0.750   0.0350   0.03024   0.02044  -0.0453   1.0000   1.0000
   1.000   0.0551   0.03110   0.02112  -0.0457   1.0000   1.0000
   1.250   0.0890   0.03254   0.02239  -0.0487   0.9943   1.0000
   1.500   0.1354   0.03424   0.02390  -0.0539   0.9783   1.0000
   1.750   0.1770   0.03574   0.02526  -0.0581   0.9638   1.0000
   2.000   0.2158   0.03710   0.02650  -0.0616   0.9496   1.0000
   2.250   0.2526   0.03837   0.02769  -0.0647   0.9356   1.0000
   2.500   0.2877   0.03959   0.02884  -0.0673   0.9216   1.0000
   2.750   0.3216   0.04075   0.02996  -0.0697   0.9075   1.0000
   3.000   0.3545   0.04189   0.03107  -0.0719   0.8934   1.0000
   3.250   0.3872   0.04301   0.03218  -0.0739   0.8791   1.0000
   3.500   0.4192   0.04411   0.03329  -0.0757   0.8646   1.0000
   3.750   0.4515   0.04518   0.03437  -0.0774   0.8499   1.0000
   4.000   0.4830   0.04623   0.03545  -0.0790   0.8353   1.0000
   4.250   0.5155   0.04722   0.03652  -0.0805   0.8202   1.0000
   4.500   0.5488   0.04816   0.03752  -0.0820   0.8050   1.0000
   4.750   0.5823   0.04903   0.03846  -0.0834   0.7899   1.0000
   5.000   0.6181   0.04979   0.03932  -0.0849   0.7745   1.0000
   5.250   0.6382   0.05077   0.04042  -0.0845   0.7572   1.0000
   5.500   0.6637   0.05163   0.04139  -0.0847   0.7400   1.0000
   5.750   0.6936   0.05232   0.04221  -0.0851   0.7230   1.0000
   6.000   0.7288   0.05270   0.04277  -0.0858   0.7061   1.0000
   6.250   0.7701   0.05263   0.04289  -0.0867   0.6894   1.0000
   6.500   0.7979   0.05303   0.04346  -0.0863   0.6710   1.0000
   6.750   0.8231   0.05346   0.04405  -0.0855   0.6513   1.0000
   7.000   0.8695   0.05230   0.04319  -0.0857   0.6333   1.0000
   7.250   0.9348   0.04910   0.04034  -0.0861   0.6167   1.0000
   7.500   0.9614   0.04856   0.04006  -0.0841   0.5946   1.0000
   7.750   1.1017   0.03875   0.03091  -0.0887   0.5704   1.0000
   8.000   1.1639   0.03535   0.02778  -0.0889   0.5327   1.0000
   8.250   1.2105   0.03330   0.02570  -0.0880   0.4868   1.0000
   8.500   1.2330   0.03300   0.02524  -0.0850   0.4404   1.0000
   8.750   1.2446   0.03355   0.02559  -0.0812   0.3948   1.0000
   9.000   1.2527   0.03456   0.02633  -0.0773   0.3501   1.0000
   9.250   1.2594   0.03594   0.02746  -0.0736   0.3078   1.0000
   9.500   1.2677   0.03766   0.02881  -0.0703   0.2678   1.0000
   9.750   1.2701   0.03962   0.03065  -0.0666   0.2349   1.0000
  10.000   1.2766   0.04179   0.03263  -0.0635   0.2044   1.0000
  10.250   1.2858   0.04422   0.03493  -0.0610   0.1774   1.0000
  10.500   1.3003   0.04693   0.03746  -0.0594   0.1535   1.0000
  10.750   1.3091   0.04973   0.04038  -0.0571   0.1366   1.0000
  11.000   1.3233   0.05302   0.04381  -0.0556   0.1232   1.0000
  11.250   1.3350   0.05627   0.04721  -0.0540   0.1127   1.0000
  11.500   1.3402   0.05970   0.05098  -0.0516   0.1064   1.0000
  11.750   1.3531   0.06419   0.05564  -0.0506   0.1012   1.0000
  12.000   1.3367   0.06759   0.05948  -0.0464   0.0998   1.0000
  12.250   1.3187   0.07130   0.06358  -0.0429   0.0987   1.0000
  12.500   1.2981   0.07530   0.06793  -0.0401   0.0979   1.0000
  12.750   1.2750   0.07979   0.07272  -0.0380   0.0977   1.0000
  13.000   1.2497   0.08485   0.07807  -0.0369   0.0981   1.0000
  13.250   1.2225   0.09056   0.08402  -0.0369   0.0989   1.0000
  13.500   1.1951   0.09693   0.09059  -0.0379   0.0999   1.0000
  13.750   1.1691   0.10392   0.09775  -0.0399   0.1009   1.0000
  14.000   1.1454   0.11143   0.10536  -0.0428   0.1018   1.0000
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