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GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
Reynolds number: 200,000
Max Cl/Cd: 77.62 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe115-il-200000.txt
Download as CSV file: xf-goe115-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 115 (MVA MK.2) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2907   0.08941   0.08615  -0.0398   1.0000   0.0505
  -9.250  -0.3006   0.08505   0.08185  -0.0426   1.0000   0.0538
  -9.000  -0.3135   0.08064   0.07752  -0.0458   1.0000   0.0546
  -8.750  -0.3247   0.07640   0.07334  -0.0481   1.0000   0.0549
  -8.500  -0.3013   0.07458   0.07152  -0.0421   1.0000   0.0594
  -8.250  -0.3035   0.07162   0.06861  -0.0419   1.0000   0.0620
  -8.000  -0.3146   0.06828   0.06535  -0.0421   1.0000   0.0646
  -7.000  -0.4300   0.06826   0.06543  -0.0415   0.9974   0.0610
  -6.750  -0.3994   0.05235   0.04920  -0.0679   0.9856   0.0700
  -6.500  -0.3714   0.04599   0.04243  -0.0777   0.9763   0.0829
  -6.250  -0.3388   0.04344   0.03987  -0.0813   0.9713   0.0968
  -6.000  -0.3067   0.04380   0.04038  -0.0810   0.9655   0.1119
  -5.750  -0.2728   0.04227   0.03876  -0.0843   0.9590   0.1372
  -5.250  -0.1985   0.02107   0.01442  -0.0941   0.9435   0.0501
  -5.000  -0.1643   0.01914   0.01215  -0.0950   0.9352   0.0494
  -4.750  -0.1271   0.01778   0.01059  -0.0966   0.9284   0.0518
  -4.500  -0.0956   0.01652   0.00919  -0.0970   0.9179   0.0523
  -4.250  -0.0639   0.01551   0.00809  -0.0974   0.9077   0.0535
  -4.000  -0.0335   0.01462   0.00712  -0.0977   0.8972   0.0560
  -3.750  -0.0064   0.01380   0.00626  -0.0974   0.8847   0.0579
  -3.500   0.0202   0.01329   0.00564  -0.0969   0.8712   0.0603
  -3.250   0.0469   0.01294   0.00514  -0.0964   0.8577   0.0633
  -3.000   0.0735   0.01266   0.00471  -0.0959   0.8445   0.0688
  -2.750   0.0999   0.01230   0.00426  -0.0954   0.8320   0.0798
  -2.500   0.1242   0.01152   0.00409  -0.0949   0.8200   0.2376
  -2.250   0.1516   0.01164   0.00414  -0.0945   0.8090   0.2843
  -2.000   0.1787   0.01173   0.00412  -0.0942   0.7983   0.3069
  -1.750   0.2051   0.01180   0.00412  -0.0938   0.7869   0.3243
  -1.500   0.2317   0.01190   0.00412  -0.0934   0.7769   0.3451
  -1.250   0.2588   0.01188   0.00404  -0.0931   0.7687   0.3559
  -1.000   0.2852   0.01187   0.00402  -0.0929   0.7592   0.3667
  -0.750   0.3123   0.01188   0.00398  -0.0927   0.7518   0.3780
  -0.500   0.3390   0.01188   0.00396  -0.0924   0.7437   0.3905
  -0.250   0.3656   0.01185   0.00398  -0.0922   0.7368   0.4079
   0.000   0.3920   0.01182   0.00401  -0.0919   0.7295   0.4268
   0.250   0.4189   0.01181   0.00403  -0.0918   0.7237   0.4465
   0.500   0.4453   0.01177   0.00408  -0.0916   0.7172   0.4622
   0.750   0.4723   0.01170   0.00410  -0.0914   0.7121   0.4808
   1.000   0.4978   0.01160   0.00420  -0.0910   0.7051   0.5113
   1.250   0.5215   0.01122   0.00425  -0.0901   0.6989   0.6229
   1.500   0.5745   0.01056   0.00427  -0.0951   0.6918   1.0000
   1.750   0.6014   0.01070   0.00433  -0.0949   0.6855   1.0000
   2.000   0.6279   0.01087   0.00446  -0.0946   0.6793   1.0000
   2.250   0.6543   0.01102   0.00458  -0.0942   0.6725   1.0000
   2.500   0.6812   0.01119   0.00471  -0.0940   0.6669   1.0000
   2.750   0.7071   0.01138   0.00494  -0.0937   0.6609   1.0000
   3.000   0.7342   0.01156   0.00513  -0.0935   0.6559   1.0000
   3.250   0.7604   0.01178   0.00540  -0.0932   0.6505   1.0000
   3.500   0.7867   0.01199   0.00566  -0.0929   0.6449   1.0000
   3.750   0.8136   0.01217   0.00584  -0.0926   0.6386   1.0000
   4.000   0.8388   0.01220   0.00587  -0.0917   0.6257   1.0000
   4.250   0.8621   0.01216   0.00586  -0.0904   0.6082   1.0000
   4.500   0.8849   0.01208   0.00578  -0.0890   0.5871   1.0000
   4.750   0.9075   0.01203   0.00573  -0.0876   0.5649   1.0000
   5.000   0.9283   0.01196   0.00570  -0.0858   0.5317   1.0000
   5.250   0.9376   0.01232   0.00552  -0.0817   0.3898   1.0000
   5.500   0.9170   0.01617   0.00735  -0.0747   0.0755   1.0000
   5.750   0.9299   0.01748   0.00863  -0.0722   0.0520   1.0000
   6.000   0.9413   0.01877   0.01001  -0.0695   0.0444   1.0000
   6.250   0.9557   0.01976   0.01110  -0.0673   0.0415   1.0000
   6.500   0.9684   0.02087   0.01227  -0.0648   0.0390   1.0000
   6.750   0.9806   0.02203   0.01349  -0.0624   0.0369   1.0000
   7.000   0.9899   0.02365   0.01507  -0.0597   0.0338   1.0000
   7.250   1.0068   0.02563   0.01703  -0.0580   0.0324   1.0000
   7.500   1.0301   0.02702   0.01849  -0.0571   0.0315   1.0000
   7.750   1.0586   0.02888   0.02044  -0.0570   0.0309   1.0000
   8.000   1.0901   0.03119   0.02287  -0.0572   0.0308   1.0000
   8.250   1.1146   0.03292   0.02481  -0.0564   0.0294   1.0000
   8.500   1.1411   0.03551   0.02764  -0.0559   0.0293   1.0000
   8.750   1.1679   0.03972   0.03212  -0.0555   0.0311   1.0000
  16.500   0.7571   0.19177   0.18884  -0.0833   0.0410   1.0000
  16.750   0.7577   0.19564   0.19272  -0.0856   0.0383   1.0000
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