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GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 415 AIRFOIL (goe415-il)
Reynolds number: 500,000
Max Cl/Cd: 90.88 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe415-il-500000-n5.txt
Download as CSV file: xf-goe415-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 415 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3807   0.09322   0.09117  -0.0105   1.0000   0.0073
  -7.750  -0.3751   0.08970   0.08768  -0.0125   1.0000   0.0074
  -7.500  -0.3701   0.08622   0.08423  -0.0145   1.0000   0.0074
  -7.250  -0.3640   0.08260   0.08063  -0.0173   1.0000   0.0074
  -5.750  -0.2407   0.05153   0.04930  -0.0548   0.9284   0.0071
  -5.250  -0.1933   0.04156   0.03896  -0.0627   0.8975   0.0065
  -4.750  -0.1398   0.03199   0.02877  -0.0667   0.8676   0.0070
  -4.500  -0.1154   0.02817   0.02461  -0.0676   0.8495   0.0066
  -4.250  -0.0901   0.02471   0.02075  -0.0677   0.8263   0.0063
  -4.000  -0.0648   0.02154   0.01707  -0.0672   0.7892   0.0061
  -3.750  -0.0396   0.01872   0.01365  -0.0662   0.7454   0.0060
  -3.500  -0.0135   0.01622   0.01056  -0.0653   0.7087   0.0061
  -3.250   0.0130   0.01416   0.00799  -0.0645   0.6771   0.0066
  -3.000   0.0395   0.01290   0.00633  -0.0638   0.6447   0.0071
  -2.750   0.0657   0.01220   0.00535  -0.0634   0.6118   0.0081
  -2.500   0.0924   0.01188   0.00485  -0.0631   0.5814   0.0089
  -2.250   0.1192   0.01137   0.00414  -0.0627   0.5584   0.0097
  -2.000   0.1463   0.01092   0.00353  -0.0624   0.5410   0.0108
  -1.500   0.2009   0.01018   0.00253  -0.0620   0.5136   0.0155
  -1.250   0.2286   0.01000   0.00225  -0.0618   0.5019   0.0189
  -1.000   0.2564   0.00997   0.00214  -0.0617   0.4915   0.0225
  -0.750   0.2840   0.00977   0.00185  -0.0616   0.4816   0.0278
  -0.500   0.3118   0.00972   0.00171  -0.0615   0.4714   0.0329
  -0.250   0.3396   0.00964   0.00156  -0.0614   0.4611   0.0409
   0.000   0.3661   0.00902   0.00149  -0.0615   0.4503   0.2555
   0.250   0.3929   0.00874   0.00149  -0.0615   0.4386   0.3817
   0.500   0.4198   0.00854   0.00151  -0.0614   0.4270   0.4847
   0.750   0.4423   0.00782   0.00157  -0.0604   0.4166   0.7573
   1.250   0.5072   0.00756   0.00157  -0.0621   0.3904   1.0000
   1.500   0.5344   0.00771   0.00161  -0.0619   0.3756   1.0000
   1.750   0.5616   0.00786   0.00165  -0.0618   0.3620   1.0000
   2.000   0.5888   0.00801   0.00171  -0.0617   0.3503   1.0000
   2.250   0.6159   0.00817   0.00179  -0.0615   0.3391   1.0000
   2.500   0.6431   0.00831   0.00188  -0.0614   0.3289   1.0000
   2.750   0.6702   0.00848   0.00197  -0.0613   0.3191   1.0000
   3.000   0.6972   0.00866   0.00209  -0.0612   0.3088   1.0000
   3.250   0.7243   0.00881   0.00221  -0.0611   0.2996   1.0000
   3.500   0.7514   0.00898   0.00234  -0.0609   0.2913   1.0000
   3.750   0.7783   0.00915   0.00249  -0.0608   0.2834   1.0000
   4.000   0.8054   0.00932   0.00264  -0.0607   0.2773   1.0000
   4.250   0.8323   0.00950   0.00280  -0.0606   0.2696   1.0000
   4.500   0.8591   0.00968   0.00298  -0.0605   0.2620   1.0000
   4.750   0.8859   0.00987   0.00318  -0.0603   0.2554   1.0000
   5.000   0.9126   0.01007   0.00338  -0.0602   0.2477   1.0000
   5.250   0.9388   0.01033   0.00359  -0.0600   0.2319   1.0000
   5.500   0.9647   0.01063   0.00384  -0.0598   0.2146   1.0000
   5.750   0.9900   0.01102   0.00413  -0.0596   0.1898   1.0000
   6.000   1.0116   0.01198   0.00469  -0.0590   0.1229   1.0000
   6.250   1.0286   0.01371   0.00586  -0.0579   0.0255   1.0000
   6.500   1.0525   0.01432   0.00648  -0.0574   0.0123   1.0000
   6.750   1.0770   0.01482   0.00711  -0.0569   0.0087   1.0000
   7.000   1.1015   0.01530   0.00769  -0.0565   0.0075   1.0000
   7.250   1.1251   0.01589   0.00838  -0.0560   0.0065   1.0000
   7.500   1.1477   0.01661   0.00922  -0.0553   0.0056   1.0000
   7.750   1.1706   0.01725   0.00995  -0.0547   0.0049   1.0000
   8.000   1.1923   0.01802   0.01082  -0.0540   0.0044   1.0000
   8.250   1.2128   0.01891   0.01183  -0.0531   0.0041   1.0000
   8.500   1.2290   0.02028   0.01334  -0.0518   0.0038   1.0000
   8.750   1.2467   0.02138   0.01457  -0.0506   0.0036   1.0000
   9.000   1.2622   0.02263   0.01596  -0.0491   0.0035   1.0000
   9.250   1.2772   0.02382   0.01727  -0.0477   0.0032   1.0000
   9.500   1.2924   0.02490   0.01845  -0.0463   0.0029   1.0000
   9.750   1.3063   0.02600   0.01965  -0.0449   0.0027   1.0000
  10.000   1.3165   0.02734   0.02108  -0.0432   0.0025   1.0000
  10.250   1.3201   0.02890   0.02274  -0.0406   0.0024   1.0000
  10.500   1.3178   0.03093   0.02488  -0.0378   0.0024   1.0000
  10.750   1.3143   0.03332   0.02740  -0.0356   0.0023   1.0000
  11.000   1.3143   0.03566   0.02988  -0.0341   0.0023   1.0000
  11.250   1.3131   0.03834   0.03271  -0.0330   0.0022   1.0000
  11.500   1.3111   0.04135   0.03588  -0.0323   0.0021   1.0000
  11.750   1.3089   0.04461   0.03930  -0.0319   0.0021   1.0000
  12.000   1.3060   0.04808   0.04292  -0.0316   0.0020   1.0000
  12.250   1.3029   0.05170   0.04670  -0.0316   0.0020   1.0000
  12.500   1.2988   0.05554   0.05075  -0.0316   0.0019   1.0000
  12.750   1.2938   0.05962   0.05500  -0.0320   0.0019   1.0000
  13.000   1.2873   0.06399   0.05954  -0.0327   0.0019   1.0000
  13.250   1.2795   0.06869   0.06441  -0.0339   0.0019   1.0000
  13.500   1.2702   0.07370   0.06959  -0.0354   0.0019   1.0000
  13.750   1.2595   0.07901   0.07506  -0.0372   0.0019   1.0000
  14.000   1.2477   0.08466   0.08088  -0.0394   0.0019   1.0000
  14.250   1.2355   0.09054   0.08692  -0.0420   0.0019   1.0000
  14.500   1.2227   0.09677   0.09330  -0.0448   0.0019   1.0000
  14.750   1.2100   0.10325   0.09992  -0.0480   0.0019   1.0000
  15.000   1.1967   0.11003   0.10685  -0.0514   0.0019   1.0000
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