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GOE 8K AIRFOIL (goe08k-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 8K AIRFOIL (goe08k-il)
Reynolds number: 100,000
Max Cl/Cd: 24.09 at α=11.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe08k-il-100000-n5.txt
Download as CSV file: xf-goe08k-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 8K 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.1595   0.11003   0.10464  -0.1141   0.8942   0.0339
  -9.250  -0.1786   0.10919   0.10387  -0.1087   0.8863   0.0337
  -9.000  -0.1785   0.10607   0.10077  -0.1091   0.8834   0.0333
  -8.750  -0.1794   0.10223   0.09694  -0.1105   0.8813   0.0332
  -8.500  -0.1780   0.09846   0.09318  -0.1125   0.8796   0.0329
  -8.250  -0.2063   0.09778   0.09259  -0.1065   0.8714   0.0329
  -8.000  -0.2147   0.09441   0.08925  -0.1069   0.8679   0.0326
  -7.750  -0.2262   0.09040   0.08524  -0.1084   0.8653   0.0326
  -7.500  -0.2579   0.09021   0.08513  -0.1013   0.8575   0.0322
  -7.250  -0.2727   0.08642   0.08133  -0.1010   0.8535   0.0327
  -7.000  -0.2799   0.08129   0.07611  -0.1020   0.8509   0.0328
  -6.750  -0.2993   0.07994   0.07477  -0.0969   0.8444   0.0322
  -6.500  -0.3134   0.07454   0.06920  -0.0957   0.8398   0.0334
  -6.250  -0.3129   0.07034   0.06483  -0.0949   0.8375   0.0331
  -6.000  -0.3128   0.06452   0.05865  -0.0941   0.8356   0.0336
  -5.750  -0.3326   0.06246   0.05642  -0.0875   0.8297   0.0338
  -5.500  -0.3365   0.05798   0.05148  -0.0838   0.8260   0.0343
  -5.250  -0.3290   0.05514   0.04836  -0.0817   0.8238   0.0352
  -5.000  -0.3111   0.05462   0.04783  -0.0811   0.8223   0.0370
  -4.750  -0.2960   0.05255   0.04544  -0.0796   0.8211   0.0389
  -4.500  -0.3060   0.05154   0.04421  -0.0735   0.8162   0.0399
  -4.250  -0.3016   0.04936   0.04159  -0.0695   0.8129   0.0415
  -4.000  -0.2915   0.04684   0.03824  -0.0657   0.8104   0.0451
  -3.750  -0.2743   0.04558   0.03687  -0.0645   0.8088   0.0467
  -3.500  -0.2546   0.04456   0.03563  -0.0632   0.8075   0.0491
  -3.250  -0.2333   0.04352   0.03415  -0.0619   0.8064   0.0536
  -3.000  -0.2380   0.04338   0.03367  -0.0561   0.8011   0.0555
  -2.750  -0.2240   0.04250   0.03264  -0.0540   0.7983   0.0584
  -2.500  -0.2049   0.04193   0.03195  -0.0527   0.7963   0.0621
  -2.250  -0.1822   0.04127   0.03099  -0.0517   0.7947   0.0657
  -2.000  -0.1570   0.04082   0.03020  -0.0512   0.7933   0.0694
  -1.750  -0.1288   0.03990   0.02925  -0.0517   0.7921   0.0732
  -1.500  -0.1267   0.04008   0.02937  -0.0476   0.7872   0.0757
  -1.250  -0.1089   0.03989   0.02906  -0.0461   0.7841   0.0783
  -1.000  -0.0847   0.03961   0.02865  -0.0457   0.7818   0.0806
  -0.750  -0.0579   0.03943   0.02834  -0.0457   0.7799   0.0841
  -0.500  -0.0299   0.03896   0.02789  -0.0461   0.7786   0.0872
  -0.250  -0.0002   0.03870   0.02759  -0.0466   0.7773   0.0893
   0.000  -0.0013   0.03909   0.02798  -0.0421   0.7702   0.0906
   0.250   0.0231   0.03903   0.02785  -0.0418   0.7672   0.0925
   0.500   0.0521   0.03895   0.02769  -0.0423   0.7651   0.0956
   0.750   0.0837   0.03884   0.02751  -0.0433   0.7635   0.1009
   1.250   0.1170   0.03939   0.02802  -0.0406   0.7537   0.1094
   1.500   0.1525   0.03953   0.02813  -0.0427   0.7513   0.1180
   1.750   0.3734   0.04024   0.03139  -0.0872   0.7598   1.0000
   2.000   0.3856   0.04082   0.03189  -0.0850   0.7539   1.0000
   2.250   0.4119   0.04100   0.03194  -0.0851   0.7511   1.0000
   2.500   0.4417   0.04104   0.03188  -0.0856   0.7490   1.0000
   3.000   0.4708   0.04213   0.03287  -0.0822   0.7378   1.0000
   3.250   0.4991   0.04219   0.03286  -0.0825   0.7352   1.0000
   3.500   0.5295   0.04220   0.03281  -0.0832   0.7334   1.0000
   3.750   0.5323   0.04317   0.03378  -0.0798   0.7241   1.0000
   4.000   0.5591   0.04325   0.03383  -0.0798   0.7209   1.0000
   4.250   0.5896   0.04319   0.03375  -0.0805   0.7188   1.0000
   4.750   0.6201   0.04425   0.03483  -0.0774   0.7060   1.0000
   5.000   0.6512   0.04409   0.03467  -0.0781   0.7037   1.0000
   5.500   0.6828   0.04511   0.03576  -0.0752   0.6904   1.0000
   5.750   0.7134   0.04492   0.03562  -0.0758   0.6881   1.0000
   6.250   0.7458   0.04588   0.03667  -0.0731   0.6742   1.0000
   6.500   0.7768   0.04560   0.03647  -0.0737   0.6721   1.0000
   6.750   0.7798   0.04679   0.03772  -0.0706   0.6605   1.0000
   7.000   0.8096   0.04653   0.03753  -0.0710   0.6578   1.0000
   7.500   0.8432   0.04743   0.03861  -0.0686   0.6434   1.0000
   8.000   0.8798   0.04801   0.03940  -0.0664   0.6288   1.0000
  11.500   1.1385   0.04726   0.03852  -0.0455   0.2715   1.0000
  11.750   1.1311   0.04972   0.04060  -0.0421   0.2178   1.0000
  12.000   1.1254   0.05217   0.04277  -0.0391   0.1656   1.0000
  12.250   1.1194   0.05476   0.04500  -0.0362   0.1105   1.0000
  12.500   1.1145   0.05733   0.04727  -0.0336   0.0807   1.0000
  12.750   1.1139   0.05961   0.04949  -0.0314   0.0618   1.0000
  13.000   1.1155   0.06176   0.05165  -0.0294   0.0509   1.0000
  13.500   1.1201   0.06603   0.05605  -0.0260   0.0411   1.0000
  13.750   1.1222   0.06825   0.05838  -0.0244   0.0376   1.0000
  14.000   1.1225   0.07067   0.06087  -0.0228   0.0351   1.0000
  14.250   1.1217   0.07321   0.06350  -0.0212   0.0330   1.0000
  14.500   1.1257   0.07530   0.06576  -0.0199   0.0308   1.0000
  14.750   1.1291   0.07746   0.06805  -0.0185   0.0292   1.0000
  15.000   1.1340   0.07945   0.07016  -0.0173   0.0281   1.0000
  15.250   1.1387   0.08149   0.07228  -0.0163   0.0268   1.0000
  15.500   1.1434   0.08352   0.07437  -0.0152   0.0255   1.0000
  15.750   1.1526   0.08498   0.07586  -0.0139   0.0242   1.0000
  16.000   1.1615   0.08668   0.07778  -0.0129   0.0232   1.0000
  16.250   1.1708   0.08843   0.07973  -0.0119   0.0220   1.0000
  16.500   1.1793   0.09025   0.08172  -0.0111   0.0217   1.0000
  16.750   1.1832   0.09260   0.08423  -0.0104   0.0207   1.0000
  17.000   1.1850   0.09516   0.08689  -0.0099   0.0197   1.0000
  17.250   1.1893   0.09750   0.08935  -0.0093   0.0192   1.0000
  17.500   1.1947   0.09984   0.09178  -0.0087   0.0187   1.0000
  17.750   1.1929   0.10311   0.09529  -0.0083   0.0185   1.0000
  18.000   1.1873   0.10695   0.09942  -0.0081   0.0184   1.0000
  18.250   1.1782   0.11133   0.10410  -0.0083   0.0181   1.0000
  18.500   1.1689   0.11580   0.10883  -0.0087   0.0181   1.0000
  18.750   1.1549   0.12110   0.11442  -0.0098   0.0178   1.0000
  19.000   1.1408   0.12664   0.12022  -0.0113   0.0178   1.0000
  19.250   1.1276   0.13217   0.12596  -0.0132   0.0179   1.0000
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