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GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 565 AIRFOIL (goe565-il)
Reynolds number: 50,000
Max Cl/Cd: 39.07 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe565-il-50000-n5.txt
Download as CSV file: xf-goe565-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 565 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4288   0.09823   0.09094  -0.0316   1.0000   0.0664
  -8.750  -0.4312   0.09453   0.08733  -0.0327   1.0000   0.0656
  -8.500  -0.4350   0.09107   0.08395  -0.0335   1.0000   0.0661
  -8.250  -0.4409   0.08768   0.08067  -0.0342   1.0000   0.0660
  -8.000  -0.4489   0.08432   0.07742  -0.0349   1.0000   0.0665
  -7.750  -0.4542   0.08035   0.07354  -0.0367   1.0000   0.0666
  -7.500  -0.4588   0.07603   0.06929  -0.0389   1.0000   0.0668
  -7.250  -0.4623   0.07140   0.06467  -0.0412   1.0000   0.0666
  -7.000  -0.4648   0.06649   0.05973  -0.0433   1.0000   0.0665
  -6.750  -0.4655   0.06145   0.05458  -0.0452   1.0000   0.0662
  -6.500  -0.4634   0.05651   0.04944  -0.0466   1.0000   0.0664
  -6.250  -0.4582   0.05171   0.04431  -0.0480   1.0000   0.0684
  -6.000  -0.4503   0.04640   0.03832  -0.0495   1.0000   0.0713
  -5.750  -0.4371   0.04333   0.03503  -0.0491   1.0000   0.0737
  -5.500  -0.4216   0.04060   0.03203  -0.0485   1.0000   0.0757
  -5.250  -0.4045   0.03820   0.02923  -0.0481   1.0000   0.0807
  -5.000  -0.3849   0.03530   0.02553  -0.0479   1.0000   0.0844
  -4.750  -0.3653   0.03312   0.02309  -0.0472   1.0000   0.0865
  -4.500  -0.3448   0.03146   0.02121  -0.0464   1.0000   0.0894
  -4.250  -0.3235   0.03012   0.01949  -0.0457   1.0000   0.0950
  -4.000  -0.3009   0.02869   0.01761  -0.0450   1.0000   0.0986
  -3.750  -0.2790   0.02737   0.01616  -0.0442   1.0000   0.1011
  -3.500  -0.2568   0.02631   0.01492  -0.0433   1.0000   0.1042
  -3.250  -0.2342   0.02542   0.01382  -0.0424   1.0000   0.1081
  -3.000  -0.2112   0.02469   0.01290  -0.0417   1.0000   0.1144
  -2.750  -0.1892   0.02400   0.01219  -0.0409   1.0000   0.1213
  -2.500  -0.1667   0.02345   0.01142  -0.0400   1.0000   0.1273
  -2.250  -0.1436   0.02286   0.01082  -0.0394   1.0000   0.1343
  -2.000  -0.1205   0.02241   0.01029  -0.0388   1.0000   0.1450
  -1.750  -0.0973   0.02192   0.00993  -0.0385   1.0000   0.1670
  -1.500  -0.0614   0.02126   0.00977  -0.0408   0.9947   0.2480
  -1.250  -0.0257   0.02055   0.00977  -0.0429   0.9878   0.4194
  -1.000   0.0025   0.01967   0.00994  -0.0426   0.9809   0.6782
  -0.750   0.0508   0.01925   0.00979  -0.0463   0.9730   1.0000
  -0.500   0.0889   0.01959   0.00982  -0.0488   0.9646   1.0000
  -0.250   0.1278   0.01994   0.00989  -0.0513   0.9562   1.0000
   0.000   0.1632   0.02023   0.00999  -0.0532   0.9464   1.0000
   0.250   0.1981   0.02051   0.01010  -0.0549   0.9363   1.0000
   0.500   0.2333   0.02077   0.01024  -0.0566   0.9258   1.0000
   0.750   0.2703   0.02102   0.01038  -0.0586   0.9155   1.0000
   1.000   0.3102   0.02121   0.01051  -0.0609   0.9051   1.0000
   1.250   0.3444   0.02136   0.01061  -0.0622   0.8920   1.0000
   1.750   0.4152   0.02153   0.01077  -0.0647   0.8652   1.0000
   2.000   0.4500   0.02158   0.01084  -0.0657   0.8517   1.0000
   2.250   0.4833   0.02161   0.01093  -0.0664   0.8379   1.0000
   2.500   0.5161   0.02162   0.01100  -0.0668   0.8238   1.0000
   2.750   0.5485   0.02159   0.01104  -0.0671   0.8085   1.0000
   3.000   0.5810   0.02147   0.01103  -0.0672   0.7914   1.0000
   3.250   0.6153   0.02121   0.01085  -0.0673   0.7724   1.0000
   3.500   0.6450   0.02096   0.01071  -0.0664   0.7477   1.0000
   3.750   0.6757   0.02069   0.01049  -0.0655   0.7207   1.0000
   4.000   0.7048   0.02057   0.01042  -0.0646   0.6929   1.0000
   4.250   0.7323   0.02059   0.01053  -0.0637   0.6654   1.0000
   4.500   0.7580   0.02071   0.01072  -0.0625   0.6353   1.0000
   4.750   0.7830   0.02087   0.01093  -0.0613   0.6025   1.0000
   5.000   0.8079   0.02109   0.01114  -0.0600   0.5673   1.0000
   5.250   0.8327   0.02141   0.01145  -0.0587   0.5320   1.0000
   5.500   0.8556   0.02190   0.01188  -0.0572   0.4953   1.0000
   5.750   0.8771   0.02250   0.01245  -0.0557   0.4580   1.0000
   6.000   0.8972   0.02320   0.01308  -0.0540   0.4197   1.0000
   6.250   0.9145   0.02398   0.01374  -0.0520   0.3779   1.0000
   6.500   0.9298   0.02485   0.01445  -0.0499   0.3349   1.0000
   6.750   0.9446   0.02577   0.01524  -0.0480   0.2935   1.0000
   7.000   0.9592   0.02674   0.01610  -0.0461   0.2553   1.0000
   7.250   0.9743   0.02777   0.01709  -0.0443   0.2208   1.0000
   7.500   0.9877   0.02900   0.01820  -0.0425   0.1880   1.0000
   7.750   0.9998   0.03050   0.01961  -0.0406   0.1542   1.0000
   8.000   1.0133   0.03213   0.02124  -0.0387   0.1248   1.0000
   8.250   1.0276   0.03379   0.02291  -0.0370   0.1052   1.0000
   8.500   1.0410   0.03541   0.02451  -0.0352   0.0920   1.0000
   8.750   1.0550   0.03719   0.02632  -0.0336   0.0822   1.0000
   9.000   1.0689   0.03908   0.02822  -0.0320   0.0754   1.0000
   9.250   1.0854   0.04108   0.03047  -0.0306   0.0681   1.0000
   9.500   1.0998   0.04314   0.03266  -0.0292   0.0631   1.0000
   9.750   1.1162   0.04563   0.03539  -0.0279   0.0587   1.0000
  10.000   1.1275   0.04796   0.03804  -0.0263   0.0545   1.0000
  10.250   1.1374   0.05035   0.04056  -0.0247   0.0516   1.0000
  10.500   1.1486   0.05347   0.04380  -0.0234   0.0495   1.0000
  10.750   1.1480   0.05661   0.04742  -0.0210   0.0480   1.0000
  11.000   1.1424   0.05995   0.05115  -0.0187   0.0465   1.0000
  11.250   1.1341   0.06339   0.05492  -0.0169   0.0453   1.0000
  11.500   1.1229   0.06714   0.05896  -0.0155   0.0444   1.0000
  11.750   1.1088   0.07131   0.06340  -0.0149   0.0438   1.0000
  12.000   1.0909   0.07622   0.06857  -0.0153   0.0437   1.0000
  12.250   1.0689   0.08209   0.07469  -0.0171   0.0438   1.0000
  12.500   1.0421   0.08944   0.08228  -0.0206   0.0445   1.0000
  12.750   1.0126   0.09849   0.09151  -0.0261   0.0456   1.0000
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