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


Details Polar file
Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.58 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe114-il-1000000.txt
Download as CSV file: xf-goe114-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3790   0.10969   0.10805  -0.0370   1.0000   0.0041
 -10.250  -0.3769   0.10562   0.10400  -0.0382   1.0000   0.0041
 -10.000  -0.3742   0.10210   0.10048  -0.0392   1.0000   0.0041
  -7.500  -0.3411   0.03733   0.03519  -0.1010   0.9648   0.0045
  -7.250  -0.3208   0.03332   0.03097  -0.1054   0.9539   0.0049
  -7.000  -0.3012   0.03098   0.02842  -0.1071   0.9406   0.0054
  -6.750  -0.2843   0.02859   0.02577  -0.1072   0.9254   0.0058
  -6.500  -0.2644   0.02713   0.02408  -0.1068   0.9118   0.0071
  -6.250  -0.2374   0.02739   0.02418  -0.1062   0.9004   0.0085
  -6.000  -0.2152   0.02685   0.02338  -0.1054   0.8885   0.0089
  -5.750  -0.1961   0.02496   0.02121  -0.1046   0.8774   0.0089
  -5.500  -0.1760   0.02299   0.01896  -0.1038   0.8675   0.0090
  -5.250  -0.1546   0.02114   0.01683  -0.1031   0.8588   0.0090
  -5.000  -0.1323   0.01934   0.01477  -0.1023   0.8505   0.0090
  -4.750  -0.1089   0.01765   0.01283  -0.1016   0.8427   0.0090
  -4.250  -0.0598   0.01467   0.00947  -0.1004   0.8282   0.0090
  -4.000  -0.0382   0.01128   0.00597  -0.0991   0.8218   0.0079
  -3.750  -0.0143   0.01003   0.00464  -0.0981   0.8149   0.0073
  -3.500   0.0107   0.00931   0.00379  -0.0975   0.8087   0.0080
  -3.250   0.0379   0.00912   0.00356  -0.0973   0.8021   0.0093
  -3.000   0.0622   0.00821   0.00244  -0.0967   0.7960   0.0117
  -2.750   0.0891   0.00787   0.00199  -0.0965   0.7897   0.0127
  -2.500   0.1161   0.00761   0.00161  -0.0963   0.7836   0.0142
  -2.250   0.1435   0.00745   0.00135  -0.0962   0.7775   0.0175
  -2.000   0.1708   0.00736   0.00118  -0.0961   0.7713   0.0249
  -1.750   0.1935   0.00629   0.00096  -0.0957   0.7654   0.2894
  -1.500   0.2210   0.00630   0.00094  -0.0957   0.7590   0.3065
  -1.250   0.2485   0.00629   0.00094  -0.0957   0.7527   0.3148
  -1.000   0.2760   0.00631   0.00095  -0.0957   0.7453   0.3260
  -0.750   0.3035   0.00635   0.00096  -0.0957   0.7373   0.3340
  -0.250   0.3579   0.00635   0.00094  -0.0955   0.7199   0.3417
   0.000   0.3850   0.00637   0.00093  -0.0955   0.7097   0.3449
   0.250   0.4107   0.00643   0.00090  -0.0950   0.6873   0.3478
   0.500   0.4365   0.00648   0.00090  -0.0947   0.6642   0.3515
   0.750   0.4618   0.00659   0.00093  -0.0942   0.6360   0.3553
   1.000   0.4849   0.00687   0.00099  -0.0934   0.5808   0.3586
   1.250   0.5002   0.00777   0.00122  -0.0912   0.4328   0.3619
   1.500   0.5047   0.00983   0.00199  -0.0874   0.1059   0.3650
   1.750   0.5279   0.01026   0.00223  -0.0866   0.0193   0.3697
   2.000   0.5539   0.01041   0.00242  -0.0863   0.0150   0.3741
   2.250   0.5794   0.01058   0.00270  -0.0859   0.0136   0.3788
   2.500   0.6032   0.01095   0.00321  -0.0851   0.0108   0.3833
   2.750   0.6280   0.01121   0.00351  -0.0845   0.0089   0.3878
   3.000   0.6507   0.01165   0.00407  -0.0834   0.0082   0.3929
   3.250   0.6711   0.01232   0.00485  -0.0818   0.0084   0.3981
   3.500   0.6876   0.01330   0.00594  -0.0795   0.0094   0.4032
   4.750   0.8017   0.02017   0.01329  -0.0742   0.0102   0.5068
   5.000   0.8339   0.01881   0.01314  -0.0753   0.0090   1.0000
   5.250   0.8557   0.01891   0.01327  -0.0744   0.0062   1.0000
   5.500   0.8810   0.02064   0.01495  -0.0744   0.0052   1.0000
   5.750   0.8856   0.01507   0.00992  -0.0703   0.0046   1.0000
   6.000   0.9046   0.01728   0.01235  -0.0685   0.0046   1.0000
   6.250   0.9218   0.01970   0.01499  -0.0666   0.0046   1.0000
   6.500   0.9373   0.02230   0.01784  -0.0645   0.0046   1.0000
   6.750   0.9511   0.02512   0.02089  -0.0622   0.0045   1.0000
   7.000   0.9631   0.02810   0.02408  -0.0599   0.0045   1.0000
   7.250   0.9732   0.03126   0.02745  -0.0573   0.0045   1.0000
   7.500   0.9813   0.03454   0.03095  -0.0547   0.0045   1.0000
   7.750   0.9871   0.03789   0.03450  -0.0518   0.0045   1.0000
   8.000   0.9911   0.04127   0.03807  -0.0490   0.0045   1.0000
   8.250   0.9924   0.04463   0.04161  -0.0459   0.0044   1.0000
   8.500   0.9911   0.04790   0.04505  -0.0428   0.0044   1.0000
   8.750   0.9871   0.05102   0.04833  -0.0395   0.0044   1.0000
   9.000   0.9782   0.05381   0.05127  -0.0357   0.0043   1.0000
   9.250   0.9633   0.05628   0.05385  -0.0314   0.0043   1.0000
   9.500   0.9460   0.05916   0.05685  -0.0280   0.0043   1.0000
   9.750   0.9266   0.06261   0.06042  -0.0256   0.0042   1.0000
  10.000   0.9049   0.06676   0.06469  -0.0241   0.0043   1.0000
  10.250   0.8798   0.07186   0.06990  -0.0238   0.0043   1.0000
  10.500   0.8549   0.07752   0.07567  -0.0245   0.0044   1.0000
  10.750   0.8314   0.08351   0.08177  -0.0261   0.0044   1.0000
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