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EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 66 AIRFOIL (e66-il)
Reynolds number: 50,000
Max Cl/Cd: 40.72 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e66-il-50000-n5.txt
Download as CSV file: xf-e66-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 66 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3799   0.10206   0.09533  -0.0388   1.0000   0.0505
  -8.250  -0.3872   0.09918   0.09255  -0.0382   1.0000   0.0504
  -8.000  -0.3959   0.09641   0.08989  -0.0374   1.0000   0.0498
  -7.750  -0.4071   0.09375   0.08734  -0.0363   1.0000   0.0496
  -7.500  -0.4205   0.09123   0.08494  -0.0349   1.0000   0.0491
  -7.250  -0.4333   0.08830   0.08213  -0.0342   1.0000   0.0485
  -7.000  -0.4435   0.08454   0.07847  -0.0352   1.0000   0.0479
  -6.750  -0.4518   0.07993   0.07394  -0.0375   1.0000   0.0472
  -6.250  -0.4611   0.06328   0.05701  -0.0516   1.0000   0.0442
  -6.000  -0.4531   0.05750   0.05094  -0.0555   1.0000   0.0441
  -5.750  -0.4395   0.05226   0.04534  -0.0588   1.0000   0.0444
  -5.500  -0.4212   0.04779   0.04051  -0.0616   1.0000   0.0453
  -5.250  -0.4007   0.04461   0.03704  -0.0634   1.0000   0.0473
  -5.000  -0.3756   0.04120   0.03311  -0.0658   1.0000   0.0514
  -4.750  -0.3432   0.03705   0.02797  -0.0689   0.9996   0.0551
  -4.500  -0.3082   0.03448   0.02508  -0.0717   0.9962   0.0592
  -4.250  -0.2715   0.03257   0.02255  -0.0741   0.9926   0.0680
  -4.000  -0.2380   0.03095   0.02080  -0.0759   0.9886   0.0748
  -3.750  -0.2028   0.02975   0.01936  -0.0778   0.9847   0.0876
  -3.500  -0.1700   0.02865   0.01806  -0.0791   0.9801   0.1028
  -3.250  -0.1363   0.02783   0.01717  -0.0808   0.9753   0.1288
  -3.000  -0.1005   0.02720   0.01649  -0.0829   0.9710   0.1674
  -2.750  -0.0682   0.02663   0.01599  -0.0844   0.9652   0.2122
  -2.500  -0.0321   0.02622   0.01566  -0.0867   0.9605   0.2704
  -2.250  -0.0005   0.02586   0.01547  -0.0880   0.9544   0.3337
  -2.000   0.0330   0.02561   0.01540  -0.0894   0.9489   0.4082
  -1.750   0.0638   0.02542   0.01542  -0.0902   0.9428   0.4874
  -1.500   0.0925   0.02526   0.01545  -0.0903   0.9362   0.5702
  -1.250   0.1187   0.02513   0.01553  -0.0895   0.9296   0.6569
  -1.000   0.1397   0.02496   0.01555  -0.0875   0.9220   0.7470
  -0.750   0.1588   0.02469   0.01541  -0.0850   0.9141   0.8672
  -0.500   0.1978   0.02461   0.01510  -0.0876   0.9063   1.0000
  -0.250   0.2288   0.02488   0.01509  -0.0889   0.8979   1.0000
   0.000   0.2673   0.02515   0.01507  -0.0913   0.8917   1.0000
   0.250   0.2957   0.02544   0.01517  -0.0920   0.8826   1.0000
   0.500   0.3349   0.02567   0.01521  -0.0944   0.8768   1.0000
   0.750   0.3612   0.02597   0.01536  -0.0946   0.8667   1.0000
   1.000   0.3939   0.02622   0.01549  -0.0958   0.8588   1.0000
   1.250   0.4268   0.02645   0.01562  -0.0970   0.8506   1.0000
   1.500   0.4549   0.02673   0.01583  -0.0974   0.8408   1.0000
   1.750   0.4933   0.02682   0.01586  -0.0993   0.8344   1.0000
   2.000   0.5190   0.02713   0.01613  -0.0991   0.8233   1.0000
   2.250   0.5482   0.02735   0.01633  -0.0995   0.8134   1.0000
   2.500   0.5858   0.02733   0.01632  -0.1010   0.8063   1.0000
   2.750   0.6117   0.02758   0.01659  -0.1008   0.7948   1.0000
   3.000   0.6405   0.02774   0.01678  -0.1009   0.7841   1.0000
   3.250   0.6804   0.02751   0.01662  -0.1025   0.7772   1.0000
   3.500   0.7066   0.02769   0.01687  -0.1021   0.7649   1.0000
   3.750   0.7344   0.02780   0.01706  -0.1019   0.7528   1.0000
   4.000   0.7643   0.02782   0.01720  -0.1019   0.7410   1.0000
   4.250   0.7973   0.02769   0.01718  -0.1022   0.7297   1.0000
   4.500   0.8369   0.02730   0.01691  -0.1034   0.7196   1.0000
   4.750   0.8670   0.02721   0.01699  -0.1032   0.7056   1.0000
   5.000   0.8983   0.02706   0.01698  -0.1031   0.6911   1.0000
   5.250   0.9240   0.02709   0.01715  -0.1022   0.6739   1.0000
   5.500   0.9509   0.02707   0.01727  -0.1014   0.6559   1.0000
   5.750   0.9812   0.02688   0.01728  -0.1009   0.6371   1.0000
   6.000   1.0106   0.02673   0.01727  -0.1002   0.6164   1.0000
   6.250   1.0366   0.02673   0.01739  -0.0991   0.5927   1.0000
   6.500   1.0605   0.02683   0.01759  -0.0977   0.5664   1.0000
   6.750   1.0840   0.02697   0.01786  -0.0962   0.5378   1.0000
   7.000   1.1058   0.02722   0.01816  -0.0946   0.5065   1.0000
   7.250   1.1251   0.02763   0.01855  -0.0926   0.4733   1.0000
   7.500   1.1395   0.02824   0.01917  -0.0900   0.4384   1.0000
   7.750   1.1527   0.02898   0.01983  -0.0874   0.4026   1.0000
   8.000   1.1626   0.02992   0.02073  -0.0845   0.3664   1.0000
   8.250   1.1712   0.03104   0.02177  -0.0816   0.3308   1.0000
   8.500   1.1781   0.03232   0.02299  -0.0788   0.2961   1.0000
   8.750   1.1837   0.03378   0.02435  -0.0760   0.2632   1.0000
   9.000   1.1887   0.03540   0.02587  -0.0733   0.2332   1.0000
   9.250   1.1930   0.03716   0.02756  -0.0708   0.2054   1.0000
   9.500   1.1976   0.03906   0.02941  -0.0685   0.1804   1.0000
   9.750   1.2006   0.04113   0.03140  -0.0663   0.1583   1.0000
  10.000   1.2045   0.04329   0.03356  -0.0643   0.1380   1.0000
  10.250   1.2067   0.04561   0.03582  -0.0625   0.1211   1.0000
  10.500   1.2097   0.04802   0.03827  -0.0608   0.1069   1.0000
  10.750   1.2134   0.05048   0.04078  -0.0592   0.0942   1.0000
  11.000   1.2188   0.05297   0.04340  -0.0578   0.0833   1.0000
  11.250   1.2247   0.05554   0.04612  -0.0565   0.0744   1.0000
  11.500   1.2310   0.05816   0.04868  -0.0553   0.0684   1.0000
  11.750   1.2407   0.06084   0.05174  -0.0541   0.0618   1.0000
  12.000   1.2443   0.06362   0.05452  -0.0532   0.0573   1.0000
  12.250   1.2525   0.06677   0.05804  -0.0522   0.0532   1.0000
  12.500   1.2588   0.07018   0.06177  -0.0513   0.0503   1.0000
  12.750   1.2602   0.07365   0.06545  -0.0506   0.0480   1.0000
  13.000   1.2636   0.07698   0.06883  -0.0502   0.0455   1.0000
  13.250   1.2536   0.08181   0.07406  -0.0503   0.0443   1.0000
  13.500   1.2409   0.08710   0.07974  -0.0510   0.0433   1.0000
  13.750   1.2260   0.09289   0.08587  -0.0524   0.0425   1.0000
  14.000   1.2089   0.09930   0.09257  -0.0547   0.0421   1.0000
  14.250   1.1897   0.10647   0.10001  -0.0579   0.0420   1.0000
  14.500   1.1685   0.11459   0.10832  -0.0623   0.0422   1.0000
  14.750   1.1462   0.12375   0.11767  -0.0678   0.0427   1.0000
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