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GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il)
Reynolds number: 100,000
Max Cl/Cd: 49.74 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe114-il-100000.txt
Download as CSV file: xf-goe114-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 114 (MVA MK.1) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3941   0.10169   0.09716  -0.0409   1.0000   0.1325
  -8.500  -0.3737   0.09726   0.09271  -0.0380   1.0000   0.1393
  -8.250  -0.3923   0.09607   0.09167  -0.0393   1.0000   0.1455
  -8.000  -0.3813   0.09226   0.08788  -0.0373   1.0000   0.1506
  -7.750  -0.3898   0.09059   0.08632  -0.0362   1.0000   0.1575
  -7.500  -0.3363   0.08009   0.07631  -0.0302   1.0000   0.1649
  -7.250  -0.4050   0.08648   0.08241  -0.0314   1.0000   0.1656
  -7.000  -0.4254   0.08581   0.08186  -0.0276   1.0000   0.1695
  -6.750  -0.4724   0.08619   0.08243  -0.0291   1.0000   0.1731
  -6.500  -0.4576   0.08262   0.07887  -0.0228   1.0000   0.1771
  -6.250  -0.4669   0.08093   0.07725  -0.0210   1.0000   0.1833
  -6.000  -0.4798   0.07848   0.07487  -0.0211   1.0000   0.1891
  -5.750  -0.4789   0.07629   0.07271  -0.0186   1.0000   0.1939
  -4.750  -0.4325   0.03740   0.03160  -0.0554   1.0000   0.0920
  -4.500  -0.3954   0.03266   0.02565  -0.0566   0.9980   0.0673
  -4.250  -0.3534   0.02990   0.02209  -0.0583   0.9937   0.0552
  -4.000  -0.3171   0.02694   0.01878  -0.0596   0.9892   0.0496
  -3.750  -0.2766   0.02547   0.01688  -0.0611   0.9842   0.0457
  -3.500  -0.2407   0.02383   0.01525  -0.0627   0.9794   0.0502
  -3.250  -0.2059   0.02282   0.01410  -0.0638   0.9732   0.0494
  -3.000  -0.1652   0.02209   0.01315  -0.0662   0.9681   0.0504
  -2.750  -0.1328   0.02150   0.01227  -0.0671   0.9605   0.0530
  -2.500  -0.0900   0.02091   0.01147  -0.0700   0.9555   0.0648
  -2.250  -0.0615   0.02025   0.01190  -0.0708   0.9474   0.3264
  -2.000  -0.0238   0.02110   0.01246  -0.0725   0.9404   0.3850
  -1.750   0.0061   0.02138   0.01269  -0.0731   0.9320   0.4188
  -1.500   0.0323   0.02170   0.01327  -0.0728   0.9240   0.4838
  -1.250   0.0706   0.02160   0.01300  -0.0752   0.9174   0.4952
  -1.000   0.1006   0.02157   0.01288  -0.0760   0.9089   0.5077
  -0.750   0.1425   0.02140   0.01260  -0.0789   0.9032   0.5211
  -0.500   0.1708   0.02135   0.01254  -0.0794   0.8941   0.5302
  -0.250   0.2161   0.02112   0.01229  -0.0829   0.8893   0.5408
   0.000   0.2429   0.02112   0.01229  -0.0830   0.8795   0.5499
   0.250   0.2873   0.02088   0.01210  -0.0862   0.8746   0.5629
   0.500   0.3179   0.02084   0.01212  -0.0870   0.8655   0.5764
   0.750   0.3573   0.02063   0.01204  -0.0893   0.8589   0.5945
   1.000   0.3946   0.02035   0.01197  -0.0911   0.8517   0.6203
   1.500   0.4894   0.01915   0.01188  -0.0985   0.8390   1.0000
   1.750   0.5208   0.01928   0.01198  -0.0991   0.8301   1.0000
   2.000   0.5639   0.01852   0.01123  -0.1005   0.8182   1.0000
   2.250   0.6112   0.01630   0.00901  -0.0999   0.7903   1.0000
   2.500   0.6427   0.01504   0.00782  -0.0977   0.7594   1.0000
   2.750   0.6644   0.01402   0.00669  -0.0936   0.7067   1.0000
   3.000   0.6789   0.01365   0.00590  -0.0889   0.6091   1.0000
   3.250   0.6866   0.01456   0.00576  -0.0841   0.4368   1.0000
   3.500   0.6782   0.01781   0.00695  -0.0786   0.0645   1.0000
   3.750   0.6986   0.01861   0.00775  -0.0769   0.0534   1.0000
   4.000   0.7191   0.01935   0.00870  -0.0752   0.0500   1.0000
   4.250   0.7359   0.02039   0.00992  -0.0730   0.0458   1.0000
   4.500   0.7477   0.02172   0.01151  -0.0702   0.0423   1.0000
   4.750   0.7603   0.02291   0.01280  -0.0674   0.0422   1.0000
   5.000   0.7732   0.02436   0.01423  -0.0647   0.0427   1.0000
   5.250   0.7964   0.02588   0.01568  -0.0634   0.0439   1.0000
   5.500   0.8256   0.02677   0.01672  -0.0626   0.0472   1.0000
   5.750   0.8652   0.02895   0.01893  -0.0632   0.0529   1.0000
   6.000   0.9075   0.03085   0.02103  -0.0634   0.0620   1.0000
   6.250   0.9592   0.03504   0.02535  -0.0648   0.0788   1.0000
   6.500   1.0126   0.03767   0.02867  -0.0639   0.1186   1.0000
  10.500   0.8753   0.11799   0.11373  -0.0565   0.2338   1.0000
  10.750   0.8741   0.12049   0.11628  -0.0552   0.2065   1.0000
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