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GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il)
Reynolds number: 50,000
Max Cl/Cd: 35.42 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe114-il-50000.txt
Download as CSV file: xf-goe114-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3590   0.10179   0.09539  -0.0295   1.0000   0.2579
  -8.000  -0.3726   0.10106   0.09481  -0.0291   1.0000   0.2651
  -7.750  -0.3742   0.09803   0.09189  -0.0285   1.0000   0.2670
  -7.500  -0.3713   0.09467   0.08860  -0.0276   1.0000   0.2684
  -7.250  -0.3738   0.09202   0.08605  -0.0264   1.0000   0.2697
  -7.000  -0.3816   0.08989   0.08405  -0.0247   1.0000   0.2704
  -6.750  -0.3947   0.08812   0.08242  -0.0223   1.0000   0.2705
  -6.500  -0.4110   0.08652   0.08097  -0.0199   1.0000   0.2697
  -5.500  -0.4621   0.05637   0.05059  -0.0491   1.0000   0.1155
  -5.250  -0.4502   0.04841   0.04194  -0.0547   1.0000   0.1041
  -5.000  -0.4309   0.04193   0.03425  -0.0582   1.0000   0.0948
  -4.750  -0.4110   0.03845   0.03051  -0.0578   1.0000   0.0910
  -4.500  -0.3878   0.03504   0.02647  -0.0577   1.0000   0.0863
  -4.250  -0.3622   0.03259   0.02319  -0.0570   1.0000   0.0823
  -4.000  -0.3383   0.03070   0.02091  -0.0559   1.0000   0.0811
  -3.750  -0.3156   0.02903   0.01902  -0.0546   1.0000   0.0808
  -3.500  -0.2936   0.02768   0.01750  -0.0532   1.0000   0.0818
  -3.250  -0.2712   0.02646   0.01606  -0.0523   1.0000   0.0843
  -3.000  -0.2488   0.02554   0.01499  -0.0515   1.0000   0.0918
  -2.750  -0.2230   0.02446   0.01395  -0.0516   1.0000   0.1159
  -2.500  -0.1984   0.02378   0.01425  -0.0514   1.0000   0.3086
  -2.250  -0.1855   0.02478   0.01517  -0.0486   1.0000   0.3906
  -2.000  -0.1709   0.02526   0.01559  -0.0462   1.0000   0.4378
  -1.750  -0.1554   0.02551   0.01578  -0.0440   1.0000   0.4783
  -1.500  -0.1458   0.02573   0.01625  -0.0404   1.0000   0.5410
  -1.250  -0.1329   0.02573   0.01631  -0.0376   1.0000   0.5916
  -1.000  -0.1154   0.02565   0.01603  -0.0361   1.0000   0.6251
  -0.750  -0.0935   0.02566   0.01583  -0.0362   1.0000   0.6437
  -0.500  -0.0716   0.02569   0.01573  -0.0362   1.0000   0.6618
  -0.250  -0.0490   0.02581   0.01575  -0.0366   1.0000   0.6795
   0.000  -0.0262   0.02598   0.01586  -0.0371   1.0000   0.6994
   0.250  -0.0038   0.02615   0.01609  -0.0375   1.0000   0.7252
   0.500   0.0185   0.02624   0.01634  -0.0377   1.0000   0.7697
   0.750   0.0704   0.02665   0.01694  -0.0450   0.9862   1.0000
   1.000   0.1198   0.02794   0.01785  -0.0514   0.9741   1.0000
   1.250   0.1631   0.02912   0.01874  -0.0563   0.9623   1.0000
   1.500   0.2032   0.03024   0.01964  -0.0603   0.9504   1.0000
   1.750   0.2411   0.03135   0.02058  -0.0637   0.9389   1.0000
   2.000   0.2787   0.03244   0.02157  -0.0669   0.9274   1.0000
   2.250   0.3130   0.03349   0.02257  -0.0694   0.9161   1.0000
   2.500   0.3415   0.03445   0.02352  -0.0708   0.9043   1.0000
   2.750   0.3688   0.03546   0.02461  -0.0721   0.8929   1.0000
   3.000   0.3961   0.03651   0.02571  -0.0733   0.8818   1.0000
   3.250   0.4246   0.03760   0.02689  -0.0746   0.8710   1.0000
   3.500   0.4568   0.03874   0.02816  -0.0765   0.8609   1.0000
   3.750   0.4816   0.03985   0.02943  -0.0772   0.8504   1.0000
   4.000   0.5003   0.04103   0.03076  -0.0771   0.8400   1.0000
   4.250   0.7409   0.02092   0.01128  -0.0739   0.5160   1.0000
   4.500   0.7307   0.02352   0.01182  -0.0673   0.1652   1.0000
   4.750   0.7355   0.02597   0.01362  -0.0642   0.0955   1.0000
   5.000   0.7492   0.02739   0.01513  -0.0618   0.0863   1.0000
   5.250   0.7614   0.02883   0.01672  -0.0593   0.0820   1.0000
   5.500   0.7703   0.03044   0.01847  -0.0564   0.0798   1.0000
   5.750   0.7793   0.03197   0.02011  -0.0534   0.0790   1.0000
   6.000   0.7935   0.03351   0.02179  -0.0508   0.0786   1.0000
   6.250   0.8316   0.03511   0.02354  -0.0506   0.0766   1.0000
   6.500   0.9084   0.03781   0.02629  -0.0546   0.0756   1.0000
   6.750   0.9683   0.04130   0.02991  -0.0570   0.0811   1.0000
   7.000   1.0059   0.04457   0.03385  -0.0565   0.0889   1.0000
   7.250   1.0357   0.04739   0.03732  -0.0547   0.0981   1.0000
   7.500   1.0630   0.05064   0.04116  -0.0529   0.1095   1.0000
   7.750   1.0836   0.05406   0.04531  -0.0503   0.1244   1.0000
   8.000   1.1101   0.05875   0.05052  -0.0489   0.1446   1.0000
   8.250   1.1077   0.06177   0.05451  -0.0450   0.1617   1.0000
   8.500   1.1138   0.06696   0.06030  -0.0433   0.1842   1.0000
   8.750   1.0958   0.07173   0.06561  -0.0409   0.1979   1.0000
   9.000   1.0650   0.07605   0.07024  -0.0385   0.2010   1.0000
   9.250   1.0379   0.08074   0.07506  -0.0369   0.2046   1.0000
   9.500   1.0046   0.08508   0.07945  -0.0357   0.2026   1.0000
   9.750   0.9725   0.09065   0.08503  -0.0369   0.2013   1.0000
  10.000   0.9421   0.09738   0.09172  -0.0401   0.2005   1.0000
  10.250   0.9174   0.10663   0.10092  -0.0460   0.2107   1.0000
  10.500   0.8842   0.11538   0.10953  -0.0526   0.2138   1.0000
  10.750   0.8509   0.12691   0.12080  -0.0623   0.2527   1.0000
  11.000   0.7441   0.12150   0.11588  -0.0460   0.1873   1.0000
  11.250   0.7123   0.13207   0.12639  -0.0540   0.2318   1.0000
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