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GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 5K AIRFOIL (goe05k-il)
Reynolds number: 500,000
Max Cl/Cd: 71.28 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe05k-il-500000.txt
Download as CSV file: xf-goe05k-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 5K 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5239   0.09080   0.08859  -0.0127   1.0000   0.0046
  -7.500  -0.5238   0.08776   0.08558  -0.0138   1.0000   0.0046
  -7.250  -0.5245   0.08399   0.08182  -0.0122   1.0000   0.0048
  -7.000  -0.5215   0.08058   0.07843  -0.0140   1.0000   0.0049
  -6.750  -0.5164   0.07697   0.07483  -0.0163   1.0000   0.0050
  -6.500  -0.5094   0.07331   0.07116  -0.0187   1.0000   0.0051
  -6.250  -0.5007   0.06950   0.06734  -0.0210   1.0000   0.0052
  -6.000  -0.4903   0.06561   0.06341  -0.0232   1.0000   0.0054
  -5.750  -0.4782   0.06173   0.05949  -0.0251   1.0000   0.0056
  -5.500  -0.4646   0.05784   0.05553  -0.0268   1.0000   0.0058
  -5.250  -0.4493   0.05395   0.05156  -0.0281   1.0000   0.0060
  -5.000  -0.4316   0.05015   0.04764  -0.0290   1.0000   0.0063
  -4.750  -0.4105   0.04647   0.04381  -0.0296   1.0000   0.0065
  -4.500  -0.3883   0.04289   0.04004  -0.0295   1.0000   0.0066
  -4.250  -0.3696   0.03931   0.03627  -0.0290   1.0000   0.0067
  -4.000  -0.3595   0.03588   0.03276  -0.0288   1.0000   0.0072
  -3.750  -0.3405   0.03295   0.02965  -0.0281   1.0000   0.0077
  -3.500  -0.3189   0.03002   0.02649  -0.0271   1.0000   0.0085
  -3.250  -0.2916   0.02791   0.02401  -0.0251   1.0000   0.0093
  -3.000  -0.2667   0.02406   0.01995  -0.0263   0.9990   0.0101
  -2.750  -0.2339   0.02173   0.01729  -0.0269   0.9975   0.0121
  -2.500  -0.2022   0.01904   0.01422  -0.0275   0.9962   0.0140
  -2.250  -0.1673   0.01909   0.01402  -0.0280   0.9943   0.0180
  -2.000  -0.1407   0.01529   0.00990  -0.0282   0.9934   0.0224
  -1.750  -0.1096   0.01408   0.00837  -0.0288   0.9917   0.0385
  -1.500  -0.0774   0.01238   0.00646  -0.0283   0.9908   0.0268
  -1.250  -0.0472   0.01048   0.00436  -0.0275   0.9900   0.0117
  -1.000  -0.0158   0.00948   0.00325  -0.0280   0.9886   0.0117
  -0.750   0.0157   0.00888   0.00251  -0.0286   0.9864   0.0235
  -0.500   0.0527   0.00601   0.00250  -0.0315   0.9909   1.0000
  -0.250   0.0880   0.00610   0.00246  -0.0334   0.9888   1.0000
   0.000   0.1227   0.00616   0.00243  -0.0352   0.9863   1.0000
   0.250   0.1576   0.00617   0.00240  -0.0370   0.9826   1.0000
   0.500   0.1977   0.00619   0.00240  -0.0399   0.9798   1.0000
   0.750   0.2354   0.00611   0.00234  -0.0422   0.9745   1.0000
   1.000   0.2846   0.00592   0.00221  -0.0469   0.9694   1.0000
   1.250   0.3276   0.00566   0.00208  -0.0502   0.9605   1.0000
   1.500   0.4013   0.00563   0.00104  -0.0582   0.6358   1.0000
   1.750   0.3947   0.00875   0.00175  -0.0518   0.0170   1.0000
   2.000   0.4167   0.00939   0.00251  -0.0502   0.0113   1.0000
   2.250   0.4374   0.01024   0.00345  -0.0484   0.0086   1.0000
   3.250   0.5354   0.01706   0.01095  -0.0412   0.0264   1.0000
   3.500   0.5572   0.01952   0.01353  -0.0402   0.0207   1.0000
   3.750   0.5807   0.02089   0.01528  -0.0383   0.0158   1.0000
   4.000   0.6020   0.02321   0.01793  -0.0364   0.0122   1.0000
   4.250   0.6176   0.02678   0.02162  -0.0350   0.0100   1.0000
   4.500   0.6432   0.02831   0.02365  -0.0323   0.0082   1.0000
   4.750   0.6574   0.03132   0.02683  -0.0309   0.0074   1.0000
   5.000   0.6754   0.03498   0.03088  -0.0281   0.0071   1.0000
   5.250   0.6975   0.03823   0.03445  -0.0256   0.0063   1.0000
   5.500   0.7138   0.04171   0.03818  -0.0237   0.0058   1.0000
   5.750   0.7267   0.04527   0.04194  -0.0222   0.0054   1.0000
   6.000   0.7289   0.04960   0.04636  -0.0214   0.0051   1.0000
   6.250   0.7428   0.05360   0.05059  -0.0198   0.0050   1.0000
   6.500   0.7563   0.05779   0.05499  -0.0185   0.0050   1.0000
   6.750   0.7689   0.06224   0.05963  -0.0178   0.0049   1.0000
   7.000   0.7774   0.06659   0.06413  -0.0176   0.0048   1.0000
   7.250   0.7828   0.07108   0.06872  -0.0180   0.0047   1.0000
   7.500   0.7854   0.07571   0.07344  -0.0188   0.0046   1.0000
   7.750   0.7853   0.08006   0.07785  -0.0200   0.0046   1.0000
   8.000   0.7805   0.08439   0.08221  -0.0213   0.0045   1.0000
   8.250   0.7721   0.08864   0.08648  -0.0235   0.0045   1.0000
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