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GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il)
Reynolds number: 500,000
Max Cl/Cd: 104.54 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe117-il-500000-n5.txt
Download as CSV file: xf-goe117-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 117 (MVA MK.4) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3673   0.09060   0.08845  -0.0407   1.0000   0.0064
  -9.250  -0.3674   0.08526   0.08314  -0.0440   0.9982   0.0064
  -8.750  -0.4372   0.02455   0.02123  -0.1090   0.9269   0.0061
  -8.500  -0.4124   0.02130   0.01744  -0.1114   0.9127   0.0063
  -8.250  -0.3911   0.01876   0.01446  -0.1121   0.8997   0.0067
  -8.000  -0.3671   0.01755   0.01297  -0.1122   0.8898   0.0071
  -7.750  -0.3425   0.01664   0.01184  -0.1122   0.8808   0.0075
  -7.500  -0.3179   0.01589   0.01089  -0.1120   0.8715   0.0082
  -7.250  -0.2934   0.01511   0.00990  -0.1117   0.8628   0.0089
  -6.750  -0.2449   0.01342   0.00780  -0.1109   0.8459   0.0106
  -6.500  -0.2190   0.01304   0.00732  -0.1107   0.8383   0.0116
  -6.250  -0.1930   0.01267   0.00684  -0.1104   0.8300   0.0129
  -6.000  -0.1668   0.01239   0.00642  -0.1101   0.8221   0.0142
  -5.750  -0.1406   0.01213   0.00611  -0.1099   0.8131   0.0165
  -5.500  -0.1141   0.01195   0.00586  -0.1097   0.8035   0.0188
  -5.250  -0.0877   0.01177   0.00556  -0.1094   0.7932   0.0212
  -5.000  -0.0608   0.01179   0.00547  -0.1092   0.7817   0.0226
  -4.750  -0.0357   0.01124   0.00478  -0.1087   0.7692   0.0247
  -4.500  -0.0099   0.01094   0.00439  -0.1084   0.7550   0.0269
  -4.250   0.0159   0.01074   0.00407  -0.1080   0.7379   0.0287
  -4.000   0.0414   0.01053   0.00373  -0.1076   0.7164   0.0301
  -3.750   0.0665   0.01038   0.00340  -0.1070   0.6913   0.0314
  -3.250   0.1168   0.01013   0.00281  -0.1059   0.6488   0.0328
  -3.000   0.1426   0.01001   0.00256  -0.1055   0.6343   0.0333
  -2.750   0.1687   0.00989   0.00231  -0.1052   0.6232   0.0336
  -2.500   0.1952   0.00979   0.00210  -0.1049   0.6138   0.0340
  -2.250   0.2218   0.00967   0.00188  -0.1046   0.6059   0.0357
  -2.000   0.2484   0.00956   0.00170  -0.1044   0.5985   0.0399
  -1.750   0.2751   0.00948   0.00159  -0.1042   0.5919   0.0454
  -1.500   0.3009   0.00914   0.00149  -0.1040   0.5855   0.1173
  -1.250   0.3275   0.00911   0.00146  -0.1038   0.5801   0.1443
  -1.000   0.3547   0.00909   0.00143  -0.1037   0.5751   0.1541
  -0.750   0.3815   0.00906   0.00140  -0.1035   0.5702   0.1644
  -0.500   0.4083   0.00904   0.00139  -0.1034   0.5657   0.1766
  -0.250   0.4353   0.00899   0.00140  -0.1033   0.5612   0.1956
   0.000   0.4619   0.00891   0.00147  -0.1031   0.5569   0.2443
   0.250   0.4886   0.00892   0.00153  -0.1030   0.5529   0.2767
   0.500   0.5157   0.00893   0.00156  -0.1029   0.5491   0.2902
   0.750   0.5428   0.00894   0.00160  -0.1028   0.5450   0.2997
   1.000   0.5697   0.00897   0.00164  -0.1026   0.5409   0.3093
   1.250   0.5964   0.00901   0.00169  -0.1025   0.5364   0.3196
   1.500   0.6234   0.00900   0.00174  -0.1023   0.5314   0.3315
   1.750   0.6501   0.00901   0.00182  -0.1022   0.5269   0.3492
   2.000   0.6764   0.00901   0.00190  -0.1020   0.5232   0.3809
   2.250   0.7017   0.00875   0.00203  -0.1017   0.5198   0.5196
   2.750   0.7681   0.00795   0.00230  -0.1042   0.5072   1.0000
   3.000   0.7939   0.00804   0.00238  -0.1038   0.4979   1.0000
   3.250   0.8196   0.00815   0.00250  -0.1034   0.4910   1.0000
   3.500   0.8450   0.00827   0.00261  -0.1030   0.4803   1.0000
   3.750   0.8704   0.00839   0.00273  -0.1025   0.4682   1.0000
   4.000   0.8949   0.00856   0.00286  -0.1019   0.4497   1.0000
   4.250   0.9169   0.00888   0.00302  -0.1009   0.4053   1.0000
   4.500   0.9309   0.00988   0.00349  -0.0986   0.3055   1.0000
   4.750   0.9324   0.01207   0.00470  -0.0946   0.0988   1.0000
   5.000   0.9513   0.01276   0.00521  -0.0932   0.0519   1.0000
   5.250   0.9729   0.01321   0.00560  -0.0922   0.0374   1.0000
   5.500   0.9950   0.01360   0.00600  -0.0913   0.0295   1.0000
   5.750   1.0170   0.01398   0.00640  -0.0904   0.0237   1.0000
   6.000   1.0376   0.01446   0.00687  -0.0892   0.0168   1.0000
   6.250   1.0587   0.01488   0.00733  -0.0881   0.0144   1.0000
   6.500   1.0786   0.01536   0.00785  -0.0868   0.0126   1.0000
   6.750   1.0960   0.01602   0.00857  -0.0851   0.0108   1.0000
   7.000   1.1122   0.01670   0.00933  -0.0832   0.0097   1.0000
   7.250   1.1297   0.01724   0.00993  -0.0816   0.0088   1.0000
   7.500   1.1450   0.01788   0.01063  -0.0796   0.0082   1.0000
   7.750   1.1579   0.01852   0.01133  -0.0772   0.0077   1.0000
   8.000   1.1684   0.01924   0.01210  -0.0744   0.0072   1.0000
   8.250   1.1756   0.02015   0.01308  -0.0712   0.0069   1.0000
   8.500   1.1773   0.02143   0.01446  -0.0674   0.0065   1.0000
   8.750   1.1851   0.02245   0.01561  -0.0647   0.0064   1.0000
   9.000   1.1933   0.02351   0.01676  -0.0622   0.0061   1.0000
   9.250   1.2023   0.02458   0.01792  -0.0600   0.0058   1.0000
   9.500   1.2109   0.02574   0.01916  -0.0579   0.0054   1.0000
   9.750   1.2209   0.02684   0.02034  -0.0562   0.0051   1.0000
  10.000   1.2288   0.02818   0.02175  -0.0543   0.0049   1.0000
  10.250   1.2372   0.02954   0.02319  -0.0526   0.0047   1.0000
  10.500   1.2450   0.03103   0.02476  -0.0509   0.0046   1.0000
  10.750   1.2514   0.03271   0.02652  -0.0493   0.0044   1.0000
  11.000   1.2558   0.03489   0.02883  -0.0473   0.0043   1.0000
  11.250   1.2650   0.03659   0.03069  -0.0459   0.0042   1.0000
  11.500   1.2735   0.03850   0.03276  -0.0445   0.0041   1.0000
  11.750   1.2816   0.04061   0.03508  -0.0431   0.0039   1.0000
  12.000   1.2879   0.04316   0.03786  -0.0416   0.0039   1.0000
  12.250   1.2921   0.04612   0.04113  -0.0401   0.0037   1.0000
  12.500   1.2914   0.04982   0.04515  -0.0386   0.0036   1.0000
  12.750   1.2839   0.05456   0.05026  -0.0371   0.0035   1.0000
  13.000   1.2698   0.06015   0.05620  -0.0360   0.0035   1.0000
  13.250   1.2487   0.06685   0.06325  -0.0354   0.0034   1.0000
  13.500   1.2243   0.07428   0.07099  -0.0357   0.0034   1.0000
  13.750   1.2000   0.08170   0.07866  -0.0369   0.0033   1.0000
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