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GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 517 AIRFOIL (goe517-il)
Reynolds number: 500,000
Max Cl/Cd: 102.01 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe517-il-500000-n5.txt
Download as CSV file: xf-goe517-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 517 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3142   0.09911   0.09691  -0.0296   1.0000   0.0088
  -8.500  -0.3130   0.09640   0.09423  -0.0300   1.0000   0.0088
  -8.250  -0.3136   0.09375   0.09163  -0.0301   1.0000   0.0089
  -7.750  -0.2896   0.08597   0.08387  -0.0378   0.9870   0.0089
  -7.500  -0.2757   0.08185   0.07976  -0.0426   0.9767   0.0089
  -7.250  -0.2553   0.07728   0.07517  -0.0490   0.9672   0.0089
  -7.000  -0.2302   0.07225   0.07012  -0.0567   0.9576   0.0089
  -6.500  -0.1791   0.06181   0.05957  -0.0711   0.9331   0.0063
  -6.250  -0.1529   0.05633   0.05398  -0.0785   0.9136   0.0063
  -6.000  -0.1310   0.05162   0.04914  -0.0834   0.8934   0.0063
  -5.750  -0.1107   0.04858   0.04597  -0.0863   0.8767   0.0070
  -5.500  -0.0906   0.04483   0.04209  -0.0889   0.8629   0.0071
  -5.250  -0.0695   0.04049   0.03757  -0.0913   0.8521   0.0073
  -5.000  -0.0610   0.01847   0.01409  -0.0944   0.8412   0.0065
  -4.750  -0.0398   0.01550   0.01054  -0.0937   0.8335   0.0067
  -4.500  -0.0152   0.01430   0.00905  -0.0932   0.8267   0.0070
  -4.250   0.0099   0.01326   0.00774  -0.0926   0.8197   0.0074
  -4.000   0.0354   0.01234   0.00654  -0.0921   0.8130   0.0079
  -3.750   0.0615   0.01169   0.00567  -0.0916   0.8065   0.0087
  -3.500   0.0873   0.01103   0.00488  -0.0912   0.7994   0.0096
  -3.250   0.1134   0.01057   0.00431  -0.0907   0.7924   0.0104
  -3.000   0.1396   0.01012   0.00374  -0.0903   0.7846   0.0113
  -2.750   0.1657   0.00972   0.00322  -0.0898   0.7763   0.0126
  -2.500   0.1917   0.00946   0.00291  -0.0893   0.7657   0.0148
  -2.250   0.2178   0.00920   0.00254  -0.0888   0.7542   0.0167
  -2.000   0.2436   0.00893   0.00219  -0.0883   0.7422   0.0213
  -1.750   0.2696   0.00873   0.00191  -0.0877   0.7291   0.0287
  -1.500   0.2951   0.00854   0.00175  -0.0872   0.7130   0.0502
  -1.250   0.3209   0.00849   0.00164  -0.0867   0.6947   0.0676
  -1.000   0.3464   0.00848   0.00156  -0.0861   0.6732   0.0790
  -0.750   0.3716   0.00853   0.00148  -0.0855   0.6468   0.0881
  -0.500   0.3963   0.00859   0.00143  -0.0848   0.6189   0.0980
  -0.250   0.4215   0.00865   0.00137  -0.0842   0.5957   0.1059
   0.000   0.4469   0.00870   0.00134  -0.0837   0.5778   0.1134
   0.250   0.4725   0.00874   0.00132  -0.0833   0.5632   0.1229
   0.500   0.4984   0.00877   0.00132  -0.0829   0.5518   0.1345
   1.000   0.5501   0.00880   0.00136  -0.0821   0.5312   0.1809
   1.250   0.5756   0.00875   0.00142  -0.0817   0.5225   0.2387
   1.750   0.6632   0.00731   0.00165  -0.0895   0.5041   1.0000
   2.000   0.6880   0.00744   0.00171  -0.0888   0.4949   1.0000
   2.250   0.7130   0.00754   0.00178  -0.0882   0.4861   1.0000
   2.500   0.7377   0.00767   0.00186  -0.0876   0.4772   1.0000
   2.750   0.7628   0.00778   0.00194  -0.0870   0.4670   1.0000
   3.000   0.7875   0.00791   0.00204  -0.0864   0.4548   1.0000
   3.250   0.8119   0.00806   0.00214  -0.0857   0.4400   1.0000
   3.500   0.8362   0.00822   0.00225  -0.0851   0.4226   1.0000
   3.750   0.8599   0.00843   0.00239  -0.0843   0.4011   1.0000
   4.000   0.8830   0.00868   0.00255  -0.0834   0.3775   1.0000
   4.250   0.9060   0.00896   0.00274  -0.0826   0.3563   1.0000
   4.500   0.9292   0.00924   0.00296  -0.0817   0.3393   1.0000
   4.750   0.9525   0.00951   0.00319  -0.0810   0.3242   1.0000
   5.000   0.9760   0.00977   0.00343  -0.0802   0.3126   1.0000
   5.500   1.0222   0.01035   0.00395  -0.0786   0.2841   1.0000
   5.750   1.0444   0.01072   0.00423  -0.0777   0.2596   1.0000
   6.000   1.0661   0.01113   0.00454  -0.0768   0.2319   1.0000
   6.250   1.0868   0.01163   0.00490  -0.0757   0.1986   1.0000
   6.500   1.1004   0.01276   0.00557  -0.0736   0.1181   1.0000
   7.000   1.1274   0.01507   0.00731  -0.0692   0.0157   1.0000
   7.250   1.1472   0.01563   0.00793  -0.0679   0.0120   1.0000
   7.500   1.1667   0.01619   0.00854  -0.0666   0.0097   1.0000
   7.750   1.1853   0.01681   0.00922  -0.0651   0.0082   1.0000
   8.000   1.2039   0.01740   0.00990  -0.0637   0.0074   1.0000
   8.250   1.2212   0.01806   0.01064  -0.0621   0.0067   1.0000
   8.500   1.2358   0.01890   0.01155  -0.0601   0.0061   1.0000
   8.750   1.2519   0.01956   0.01231  -0.0583   0.0055   1.0000
   9.000   1.2661   0.02027   0.01309  -0.0563   0.0050   1.0000
   9.250   1.2758   0.02112   0.01401  -0.0535   0.0047   1.0000
   9.500   1.2807   0.02222   0.01520  -0.0501   0.0045   1.0000
   9.750   1.2885   0.02319   0.01629  -0.0473   0.0043   1.0000
  10.000   1.2943   0.02432   0.01755  -0.0444   0.0041   1.0000
  10.250   1.2986   0.02561   0.01896  -0.0415   0.0040   1.0000
  10.500   1.3023   0.02702   0.02049  -0.0388   0.0038   1.0000
  10.750   1.3059   0.02853   0.02211  -0.0364   0.0037   1.0000
  11.000   1.3120   0.02992   0.02359  -0.0346   0.0035   1.0000
  11.250   1.3163   0.03151   0.02526  -0.0327   0.0033   1.0000
  11.500   1.3160   0.03365   0.02753  -0.0307   0.0033   1.0000
  11.750   1.3195   0.03552   0.02953  -0.0293   0.0030   1.0000
  12.000   1.3209   0.03772   0.03188  -0.0279   0.0029   1.0000
  12.250   1.3205   0.04022   0.03454  -0.0266   0.0028   1.0000
  12.500   1.3184   0.04301   0.03748  -0.0254   0.0028   1.0000
  12.750   1.3179   0.04574   0.04039  -0.0246   0.0027   1.0000
  13.250   1.3111   0.05222   0.04726  -0.0234   0.0026   1.0000
  13.500   1.3075   0.05569   0.05090  -0.0234   0.0025   1.0000
  13.750   1.3022   0.05947   0.05485  -0.0236   0.0024   1.0000
  14.000   1.2965   0.06349   0.05905  -0.0242   0.0024   1.0000
  14.250   1.2907   0.06769   0.06339  -0.0253   0.0023   1.0000
  14.500   1.2775   0.07325   0.06919  -0.0265   0.0024   1.0000
  14.750   1.2713   0.07787   0.07394  -0.0283   0.0023   1.0000
  15.000   1.2606   0.08344   0.07968  -0.0305   0.0023   1.0000
  15.250   1.2441   0.09028   0.08675  -0.0330   0.0023   1.0000
  15.500   1.2321   0.09659   0.09322  -0.0360   0.0023   1.0000
  15.750   1.2182   0.10358   0.10038  -0.0394   0.0023   1.0000
  16.000   1.2049   0.11072   0.10767  -0.0431   0.0022   1.0000
  16.250   1.1887   0.11882   0.11594  -0.0475   0.0022   1.0000
  16.500   1.1734   0.12708   0.12436  -0.0521   0.0022   1.0000
  16.750   1.1535   0.13682   0.13427  -0.0575   0.0023   1.0000
  17.000   1.1327   0.14733   0.14495  -0.0636   0.0023   1.0000
  17.250   1.1048   0.16088   0.15869  -0.0713   0.0024   1.0000
  17.500   1.0776   0.17589   0.17381  -0.0796   0.0025   1.0000
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