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GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 371 AIRFOIL (goe371-il)
Reynolds number: 50,000
Max Cl/Cd: 43.34 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe371-il-50000-n5.txt
Download as CSV file: xf-goe371-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 371 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3182   0.10066   0.09408  -0.0282   1.0000   0.0879
  -7.500  -0.3250   0.09934   0.09289  -0.0278   1.0000   0.0905
  -7.250  -0.3344   0.09870   0.09241  -0.0292   1.0000   0.0923
  -7.000  -0.3400   0.09791   0.09175  -0.0324   1.0000   0.0930
  -6.750  -0.3356   0.09332   0.08724  -0.0293   1.0000   0.0945
  -6.500  -0.3314   0.08990   0.08388  -0.0263   1.0000   0.0975
  -6.250  -0.3317   0.08761   0.08166  -0.0255   1.0000   0.1007
  -6.000  -0.3333   0.08572   0.07985  -0.0263   1.0000   0.1047
  -5.750  -0.3309   0.08496   0.07907  -0.0335   1.0000   0.1077
  -5.500  -0.3304   0.08098   0.07520  -0.0298   1.0000   0.1092
  -5.250  -0.3288   0.07809   0.07237  -0.0264   1.0000   0.1132
  -5.000  -0.3124   0.07674   0.07083  -0.0357   1.0000   0.1225
  -4.750  -0.3155   0.07274   0.06701  -0.0292   1.0000   0.1258
  -4.500  -0.2962   0.07054   0.06464  -0.0357   1.0000   0.1375
  -4.250  -0.2930   0.06695   0.06116  -0.0320   0.9997   0.1407
  -3.750  -0.1872   0.05562   0.04884  -0.0535   0.9882   0.0930
  -3.500  -0.1441   0.05014   0.04294  -0.0592   0.9820   0.0783
  -3.250  -0.1084   0.04600   0.03869  -0.0629   0.9749   0.0744
  -3.000  -0.0631   0.04190   0.03413  -0.0683   0.9668   0.0712
  -2.750  -0.0203   0.03876   0.03044  -0.0725   0.9579   0.0743
  -2.500   0.0241   0.03572   0.02683  -0.0765   0.9507   0.0734
  -2.250   0.0613   0.03334   0.02392  -0.0786   0.9424   0.0727
  -2.000   0.1014   0.03139   0.02140  -0.0811   0.9358   0.0748
  -1.750   0.1372   0.03001   0.01944  -0.0824   0.9274   0.0782
  -1.500   0.1744   0.02862   0.01763  -0.0840   0.9203   0.0786
  -1.250   0.2095   0.02740   0.01617  -0.0853   0.9123   0.0795
  -1.000   0.2433   0.02643   0.01498  -0.0862   0.9040   0.0809
  -0.750   0.2827   0.02561   0.01393  -0.0880   0.8967   0.0834
  -0.500   0.3171   0.02500   0.01314  -0.0890   0.8876   0.0867
  -0.250   0.3584   0.02439   0.01238  -0.0912   0.8807   0.0965
   0.000   0.3896   0.02400   0.01190  -0.0917   0.8699   0.1067
   0.250   0.4234   0.02352   0.01142  -0.0925   0.8599   0.1194
   0.500   0.4633   0.02259   0.01090  -0.0946   0.8523   0.1983
   1.000   0.5275   0.02087   0.01047  -0.0955   0.8293   1.0000
   1.250   0.5586   0.02096   0.01036  -0.0957   0.8174   1.0000
   1.500   0.5903   0.02103   0.01027  -0.0960   0.8056   1.0000
   1.750   0.6232   0.02105   0.01017  -0.0963   0.7943   1.0000
   2.000   0.6520   0.02117   0.01021  -0.0961   0.7809   1.0000
   2.250   0.6802   0.02132   0.01029  -0.0958   0.7670   1.0000
   2.500   0.7082   0.02147   0.01041  -0.0954   0.7529   1.0000
   2.750   0.7358   0.02165   0.01056  -0.0950   0.7388   1.0000
   3.000   0.7631   0.02185   0.01074  -0.0945   0.7245   1.0000
   3.250   0.7898   0.02208   0.01098  -0.0939   0.7100   1.0000
   3.500   0.8161   0.02231   0.01125  -0.0933   0.6952   1.0000
   3.750   0.8425   0.02243   0.01138  -0.0924   0.6786   1.0000
   4.000   0.8659   0.02254   0.01150  -0.0910   0.6578   1.0000
   4.250   0.8897   0.02257   0.01157  -0.0895   0.6361   1.0000
   4.500   0.9133   0.02267   0.01169  -0.0882   0.6151   1.0000
   4.750   0.9372   0.02287   0.01193  -0.0870   0.5960   1.0000
   5.000   0.9624   0.02306   0.01219  -0.0860   0.5785   1.0000
   5.250   0.9879   0.02328   0.01244  -0.0851   0.5614   1.0000
   5.500   1.0115   0.02363   0.01285  -0.0840   0.5427   1.0000
   5.750   1.0353   0.02402   0.01331  -0.0829   0.5237   1.0000
   6.000   1.0593   0.02444   0.01382  -0.0818   0.5045   1.0000
   6.250   1.0816   0.02497   0.01444  -0.0806   0.4837   1.0000
   6.500   1.1031   0.02555   0.01513  -0.0793   0.4619   1.0000
   6.750   1.1236   0.02617   0.01586  -0.0779   0.4389   1.0000
   7.000   1.1431   0.02682   0.01667  -0.0763   0.4146   1.0000
   7.250   1.1606   0.02755   0.01755  -0.0745   0.3884   1.0000
   7.500   1.1767   0.02829   0.01840  -0.0725   0.3605   1.0000
   7.750   1.1915   0.02907   0.01926  -0.0705   0.3322   1.0000
   8.000   1.2053   0.02992   0.02014  -0.0683   0.3049   1.0000
   8.250   1.2186   0.03088   0.02109  -0.0662   0.2808   1.0000
   8.500   1.2321   0.03199   0.02233  -0.0642   0.2590   1.0000
   8.750   1.2420   0.03325   0.02357  -0.0620   0.2358   1.0000
   9.000   1.2461   0.03469   0.02493  -0.0593   0.2090   1.0000
   9.250   1.2470   0.03627   0.02647  -0.0563   0.1829   1.0000
   9.500   1.2483   0.03791   0.02821  -0.0536   0.1579   1.0000
   9.750   1.2469   0.03982   0.03015  -0.0511   0.1291   1.0000
  10.000   1.2444   0.04212   0.03241  -0.0489   0.1013   1.0000
  10.250   1.2394   0.04496   0.03514  -0.0469   0.0809   1.0000
  10.500   1.2328   0.04822   0.03833  -0.0451   0.0682   1.0000
  10.750   1.2251   0.05173   0.04175  -0.0438   0.0608   1.0000
  11.000   1.2225   0.05499   0.04522  -0.0427   0.0537   1.0000
  11.250   1.2167   0.05861   0.04889  -0.0421   0.0494   1.0000
  11.500   1.2143   0.06210   0.05262  -0.0414   0.0456   1.0000
  11.750   1.2131   0.06558   0.05632  -0.0409   0.0426   1.0000
  12.000   1.2117   0.06914   0.06003  -0.0406   0.0406   1.0000
  12.250   1.2094   0.07285   0.06384  -0.0405   0.0390   1.0000
  12.500   1.2088   0.07664   0.06783  -0.0403   0.0373   1.0000
  12.750   1.2071   0.08079   0.07231  -0.0406   0.0357   1.0000
  13.000   1.2031   0.08529   0.07708  -0.0414   0.0345   1.0000
  13.250   1.1967   0.09022   0.08224  -0.0428   0.0334   1.0000
  13.500   1.1894   0.09544   0.08767  -0.0445   0.0326   1.0000
  13.750   1.1808   0.10102   0.09345  -0.0467   0.0319   1.0000
  14.000   1.1712   0.10709   0.09972  -0.0493   0.0316   1.0000
  14.250   1.1600   0.11375   0.10660  -0.0525   0.0314   1.0000
  14.500   1.1456   0.12161   0.11469  -0.0568   0.0315   1.0000
  14.750   1.1239   0.13218   0.12554  -0.0631   0.0323   1.0000
  15.000   1.0966   0.14568   0.13922  -0.0712   0.0341   1.0000
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