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EPPLER 668 AIRFOIL (e668-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 668 AIRFOIL (e668-il)
Reynolds number: 50,000
Max Cl/Cd: 27.02 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e668-il-50000-n5.txt
Download as CSV file: xf-e668-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 668 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3757   0.11258   0.10613  -0.0580   0.9803   0.0438
  -9.500  -0.3727   0.10939   0.10295  -0.0587   0.9775   0.0434
  -9.250  -0.3738   0.10524   0.09884  -0.0607   0.9745   0.0432
  -9.000  -0.3740   0.10087   0.09451  -0.0632   0.9717   0.0429
  -8.750  -0.3800   0.09672   0.09039  -0.0649   0.9681   0.0426
  -8.500  -0.3895   0.09228   0.08600  -0.0667   0.9642   0.0422
  -8.250  -0.3989   0.08744   0.08118  -0.0698   0.9604   0.0415
  -8.000  -0.4161   0.08306   0.07680  -0.0717   0.9559   0.0409
  -7.750  -0.4347   0.07902   0.07273  -0.0721   0.9508   0.0404
  -7.500  -0.4472   0.07408   0.06764  -0.0737   0.9463   0.0401
  -7.250  -0.4546   0.06934   0.06267  -0.0749   0.9421   0.0396
  -7.000  -0.4629   0.06527   0.05835  -0.0742   0.9375   0.0394
  -6.750  -0.4615   0.06089   0.05359  -0.0746   0.9336   0.0393
  -6.500  -0.4511   0.05660   0.04882  -0.0756   0.9304   0.0396
  -6.250  -0.4380   0.05287   0.04460  -0.0760   0.9275   0.0402
  -6.000  -0.4269   0.04991   0.04115  -0.0751   0.9238   0.0415
  -5.750  -0.4082   0.04672   0.03719  -0.0750   0.9207   0.0439
  -5.500  -0.3860   0.04501   0.03538  -0.0754   0.9178   0.0470
  -5.250  -0.3590   0.04288   0.03278  -0.0759   0.9154   0.0498
  -5.000  -0.3300   0.04116   0.03074  -0.0768   0.9133   0.0551
  -4.750  -0.3127   0.03993   0.02927  -0.0752   0.9096   0.0601
  -4.500  -0.2910   0.03880   0.02802  -0.0745   0.9061   0.0666
  -4.250  -0.2657   0.03775   0.02680  -0.0742   0.9029   0.0762
  -4.000  -0.2384   0.03686   0.02583  -0.0743   0.9002   0.0895
  -3.750  -0.2085   0.03604   0.02496  -0.0749   0.8977   0.1107
  -3.500  -0.1922   0.03531   0.02429  -0.0735   0.8932   0.1350
  -3.250  -0.1703   0.03449   0.02369  -0.0732   0.8893   0.1803
  -3.000  -0.1439   0.03357   0.02324  -0.0740   0.8859   0.2689
  -2.750  -0.1167   0.03263   0.02308  -0.0747   0.8830   0.4230
  -2.500  -0.1066   0.03230   0.02353  -0.0707   0.8787   0.5727
  -2.250  -0.1024   0.03258   0.02417  -0.0644   0.8731   0.6872
  -2.000  -0.0866   0.03310   0.02457  -0.0609   0.8686   0.7736
  -1.750  -0.0720   0.03352   0.02479  -0.0574   0.8643   0.8283
  -1.500  -0.0656   0.03368   0.02483  -0.0527   0.8579   0.8689
  -1.250  -0.0429   0.03385   0.02483  -0.0508   0.8535   0.9115
  -1.000   0.0123   0.03426   0.02493  -0.0555   0.8510   0.9541
  -0.750   0.0835   0.03482   0.02512  -0.0646   0.8479   0.9866
  -0.500   0.1074   0.03502   0.02513  -0.0653   0.8413   1.0000
  -0.250   0.1288   0.03517   0.02507  -0.0650   0.8361   1.0000
   0.000   0.1356   0.03531   0.02507  -0.0625   0.8283   1.0000
   0.250   0.1580   0.03556   0.02515  -0.0624   0.8224   1.0000
   0.500   0.1823   0.03588   0.02529  -0.0626   0.8169   1.0000
   0.750   0.1987   0.03620   0.02548  -0.0616   0.8090   1.0000
   1.000   0.2317   0.03657   0.02569  -0.0631   0.8045   1.0000
   1.250   0.2458   0.03698   0.02601  -0.0619   0.7957   1.0000
   1.500   0.2766   0.03736   0.02626  -0.0631   0.7902   1.0000
   1.750   0.2968   0.03781   0.02662  -0.0627   0.7824   1.0000
   2.000   0.3244   0.03821   0.02694  -0.0634   0.7758   1.0000
   2.250   0.3502   0.03864   0.02729  -0.0637   0.7689   1.0000
   2.500   0.3741   0.03906   0.02766  -0.0639   0.7610   1.0000
   2.750   0.4011   0.03947   0.02802  -0.0643   0.7541   1.0000
   3.000   0.4251   0.03988   0.02841  -0.0644   0.7458   1.0000
   3.250   0.4482   0.04032   0.02882  -0.0644   0.7375   1.0000
   3.500   0.4775   0.04061   0.02910  -0.0651   0.7303   1.0000
   3.750   0.4970   0.04111   0.02961  -0.0646   0.7205   1.0000
   4.000   0.5310   0.04124   0.02976  -0.0657   0.7147   1.0000
   4.250   0.5481   0.04180   0.03034  -0.0649   0.7036   1.0000
   4.500   0.5751   0.04207   0.03064  -0.0652   0.6956   1.0000
   4.750   0.6014   0.04232   0.03093  -0.0653   0.6867   1.0000
   5.000   0.6208   0.04282   0.03151  -0.0647   0.6758   1.0000
   5.250   0.6567   0.04264   0.03140  -0.0657   0.6699   1.0000
   5.500   0.6737   0.04322   0.03204  -0.0648   0.6576   1.0000
   5.750   0.6947   0.04363   0.03256  -0.0643   0.6464   1.0000
   6.000   0.7303   0.04325   0.03228  -0.0650   0.6398   1.0000
   6.250   0.7481   0.04377   0.03290  -0.0641   0.6270   1.0000
   6.500   0.7691   0.04412   0.03336  -0.0635   0.6151   1.0000
   6.750   0.8071   0.04331   0.03271  -0.0640   0.6089   1.0000
   7.000   0.8261   0.04368   0.03321  -0.0631   0.5956   1.0000
   7.250   0.8471   0.04389   0.03355  -0.0623   0.5828   1.0000
   7.500   0.8722   0.04376   0.03359  -0.0616   0.5711   1.0000
   7.750   0.9096   0.04258   0.03258  -0.0616   0.5630   1.0000
   8.000   0.9319   0.04260   0.03278  -0.0607   0.5488   1.0000
   8.250   0.9560   0.04246   0.03279  -0.0598   0.5345   1.0000
   8.500   0.9819   0.04215   0.03264  -0.0590   0.5197   1.0000
   8.750   1.0094   0.04169   0.03236  -0.0582   0.5039   1.0000
   9.000   1.0382   0.04114   0.03194  -0.0575   0.4867   1.0000
   9.250   1.0671   0.04059   0.03150  -0.0567   0.4675   1.0000
   9.500   1.0835   0.04113   0.03216  -0.0553   0.4453   1.0000
   9.750   1.1079   0.04101   0.03208  -0.0542   0.4225   1.0000
  10.000   1.1218   0.04181   0.03294  -0.0527   0.3982   1.0000
  10.250   1.1395   0.04230   0.03339  -0.0513   0.3739   1.0000
  10.500   1.1482   0.04360   0.03477  -0.0496   0.3494   1.0000
  10.750   1.1587   0.04475   0.03588  -0.0480   0.3255   1.0000
  11.000   1.1652   0.04634   0.03750  -0.0464   0.3021   1.0000
  11.250   1.1720   0.04790   0.03900  -0.0448   0.2800   1.0000
  11.500   1.1759   0.04985   0.04100  -0.0434   0.2583   1.0000
  11.750   1.1798   0.05183   0.04296  -0.0420   0.2382   1.0000
  12.000   1.1831   0.05394   0.04504  -0.0407   0.2196   1.0000
  12.250   1.1855   0.05628   0.04744  -0.0395   0.2017   1.0000
  12.500   1.1874   0.05875   0.04994  -0.0385   0.1851   1.0000
  12.750   1.1892   0.06132   0.05254  -0.0377   0.1699   1.0000
  13.000   1.1907   0.06401   0.05526  -0.0369   0.1561   1.0000
  13.250   1.1922   0.06678   0.05806  -0.0363   0.1437   1.0000
  13.500   1.1936   0.06960   0.06087  -0.0358   0.1326   1.0000
  13.750   1.1948   0.07267   0.06412  -0.0355   0.1219   1.0000
  14.000   1.1964   0.07578   0.06735  -0.0353   0.1126   1.0000
  14.250   1.1983   0.07877   0.07033  -0.0351   0.1046   1.0000
  14.500   1.1988   0.08220   0.07399  -0.0352   0.0969   1.0000
  14.750   1.2007   0.08545   0.07732  -0.0353   0.0904   1.0000
  15.000   1.2000   0.08913   0.08120  -0.0357   0.0844   1.0000
  15.250   1.2025   0.09238   0.08450  -0.0360   0.0794   1.0000
  15.500   1.1983   0.09688   0.08932  -0.0369   0.0749   1.0000
  15.750   1.2001   0.10019   0.09268  -0.0375   0.0707   1.0000
  16.000   1.1959   0.10488   0.09761  -0.0388   0.0675   1.0000
  16.250   1.1859   0.11068   0.10373  -0.0409   0.0650   1.0000
  16.500   1.1780   0.11611   0.10937  -0.0431   0.0625   1.0000
  16.750   1.1873   0.11813   0.11128  -0.0434   0.0591   1.0000
  17.000   1.1688   0.12600   0.11949  -0.0474   0.0583   1.0000
  17.250   1.1479   0.13483   0.12861  -0.0524   0.0578   1.0000
  17.500   1.1231   0.14519   0.13920  -0.0587   0.0578   1.0000
  17.750   1.0943   0.15763   0.15179  -0.0665   0.0581   1.0000
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