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GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 613 AIRFOIL (goe613-il)
Reynolds number: 100,000
Max Cl/Cd: 53.31 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe613-il-100000.txt
Download as CSV file: xf-goe613-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 613 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3670   0.09621   0.09180  -0.0279   1.0000   0.0859
  -7.500  -0.3917   0.09550   0.09120  -0.0258   1.0000   0.0866
  -7.250  -0.4115   0.09407   0.08986  -0.0267   1.0000   0.0872
  -7.000  -0.4300   0.09255   0.08833  -0.0298   1.0000   0.0878
  -6.750  -0.4350   0.08845   0.08428  -0.0289   1.0000   0.0887
  -6.500  -0.4269   0.08502   0.08095  -0.0225   1.0000   0.0907
  -6.250  -0.4271   0.08271   0.07867  -0.0201   1.0000   0.0928
  -6.000  -0.4293   0.08027   0.07625  -0.0193   1.0000   0.0957
  -5.750  -0.4308   0.07749   0.07343  -0.0212   1.0000   0.1000
  -5.500  -0.4302   0.07366   0.06936  -0.0270   1.0000   0.1038
  -5.250  -0.4266   0.07069   0.06654  -0.0231   1.0000   0.1059
  -5.000  -0.4212   0.06850   0.06436  -0.0212   1.0000   0.1109
  -4.750  -0.4101   0.06478   0.06035  -0.0257   1.0000   0.1197
  -4.500  -0.3933   0.06194   0.05760  -0.0251   0.9973   0.1248
  -4.250  -0.3582   0.05781   0.05324  -0.0313   0.9906   0.1373
  -4.000  -0.3233   0.05441   0.04964  -0.0362   0.9842   0.1523
  -3.750  -0.2950   0.05160   0.04673  -0.0388   0.9767   0.1688
  -3.500  -0.2606   0.04912   0.04403  -0.0428   0.9699   0.1972
  -3.250  -0.2346   0.04655   0.04150  -0.0438   0.9621   0.2165
  -3.000  -0.2049   0.04436   0.03926  -0.0456   0.9549   0.2481
  -2.000  -0.0470   0.03435   0.02780  -0.0581   0.9223   0.2449
  -1.750   0.0216   0.03019   0.02185  -0.0606   0.9173   0.1111
  -1.500   0.0594   0.02887   0.02022  -0.0619   0.9067   0.1101
  -1.250   0.1133   0.02731   0.01825  -0.0656   0.9002   0.1065
  -1.000   0.1486   0.02628   0.01704  -0.0663   0.8882   0.1055
  -0.750   0.1869   0.02524   0.01595  -0.0676   0.8781   0.1064
  -0.500   0.2362   0.02406   0.01480  -0.0708   0.8713   0.1116
  -0.250   0.2700   0.02337   0.01408  -0.0713   0.8596   0.1174
   0.000   0.3230   0.02195   0.01281  -0.0750   0.8551   0.1259
   0.250   0.3563   0.02120   0.01207  -0.0752   0.8429   0.1392
   0.500   0.4635   0.01774   0.01084  -0.0894   0.8422   1.0000
   0.750   0.4989   0.01737   0.01026  -0.0900   0.8292   1.0000
   1.000   0.5350   0.01695   0.00969  -0.0906   0.8160   1.0000
   1.250   0.5707   0.01652   0.00914  -0.0912   0.8022   1.0000
   1.500   0.6053   0.01612   0.00863  -0.0916   0.7871   1.0000
   1.750   0.6390   0.01576   0.00816  -0.0918   0.7707   1.0000
   2.000   0.6725   0.01545   0.00773  -0.0920   0.7531   1.0000
   2.250   0.7006   0.01532   0.00748  -0.0913   0.7324   1.0000
   2.500   0.7281   0.01526   0.00729  -0.0905   0.7101   1.0000
   2.750   0.7538   0.01528   0.00718  -0.0895   0.6865   1.0000
   3.000   0.7791   0.01534   0.00710  -0.0884   0.6621   1.0000
   3.250   0.8009   0.01550   0.00715  -0.0868   0.6361   1.0000
   3.500   0.8239   0.01570   0.00718  -0.0855   0.6110   1.0000
   3.750   0.8480   0.01594   0.00724  -0.0844   0.5871   1.0000
   4.000   0.8698   0.01632   0.00747  -0.0830   0.5628   1.0000
   4.250   0.8945   0.01678   0.00769  -0.0821   0.5421   1.0000
   4.500   0.9164   0.01730   0.00813  -0.0810   0.5219   1.0000
   4.750   0.9395   0.01786   0.00859  -0.0800   0.5038   1.0000
   5.000   0.9625   0.01841   0.00906  -0.0791   0.4876   1.0000
   5.250   0.9855   0.01897   0.00957  -0.0782   0.4730   1.0000
   5.500   1.0086   0.01955   0.01011  -0.0774   0.4599   1.0000
   5.750   1.0323   0.02012   0.01066  -0.0766   0.4479   1.0000
   6.000   1.0566   0.02067   0.01116  -0.0760   0.4366   1.0000
   6.250   1.0773   0.02123   0.01181  -0.0748   0.4252   1.0000
   6.500   1.0992   0.02180   0.01245  -0.0738   0.4144   1.0000
   6.750   1.1231   0.02236   0.01297  -0.0731   0.4044   1.0000
   7.000   1.1443   0.02291   0.01360  -0.0720   0.3942   1.0000
   7.250   1.1640   0.02343   0.01420  -0.0706   0.3829   1.0000
   7.500   1.1830   0.02381   0.01461  -0.0690   0.3698   1.0000
   7.750   1.2014   0.02416   0.01497  -0.0674   0.3566   1.0000
   8.000   1.2198   0.02452   0.01532  -0.0657   0.3437   1.0000
   8.250   1.2391   0.02491   0.01568  -0.0643   0.3315   1.0000
   8.500   1.2540   0.02531   0.01623  -0.0621   0.3197   1.0000
   8.750   1.2694   0.02576   0.01685  -0.0601   0.3085   1.0000
   9.000   1.2832   0.02611   0.01727  -0.0578   0.2962   1.0000
   9.250   1.2972   0.02645   0.01767  -0.0555   0.2847   1.0000
   9.500   1.3078   0.02673   0.01800  -0.0527   0.2722   1.0000
   9.750   1.3124   0.02698   0.01838  -0.0489   0.2582   1.0000
  10.000   1.3176   0.02734   0.01896  -0.0452   0.2457   1.0000
  10.250   1.3190   0.02774   0.01949  -0.0410   0.2315   1.0000
  10.500   1.3192   0.02830   0.02012  -0.0369   0.2142   1.0000
  10.750   1.3179   0.02912   0.02100  -0.0330   0.1868   1.0000
  11.000   1.3136   0.03059   0.02229  -0.0293   0.1397   1.0000
  11.250   1.2995   0.03322   0.02449  -0.0254   0.0917   1.0000
  11.500   1.2879   0.03601   0.02706  -0.0222   0.0669   1.0000
  11.750   1.2785   0.03879   0.02979  -0.0196   0.0579   1.0000
  12.000   1.2703   0.04161   0.03268  -0.0175   0.0537   1.0000
  12.250   1.2595   0.04484   0.03599  -0.0158   0.0513   1.0000
  12.500   1.2520   0.04799   0.03932  -0.0147   0.0495   1.0000
  12.750   1.2432   0.05149   0.04300  -0.0140   0.0482   1.0000
  13.000   1.2324   0.05543   0.04713  -0.0138   0.0469   1.0000
  13.250   1.2222   0.05956   0.05142  -0.0141   0.0462   1.0000
  13.500   1.2108   0.06409   0.05609  -0.0147   0.0453   1.0000
  13.750   1.2018   0.06849   0.06063  -0.0155   0.0448   1.0000
  14.000   1.1940   0.07278   0.06502  -0.0163   0.0441   1.0000
  14.250   1.1885   0.07663   0.06892  -0.0167   0.0432   1.0000
  14.500   1.1926   0.07869   0.07095  -0.0155   0.0420   1.0000
  14.750   1.1991   0.08090   0.07328  -0.0150   0.0410   1.0000
  15.000   1.2054   0.08322   0.07572  -0.0145   0.0399   1.0000
  15.250   1.2130   0.08540   0.07800  -0.0138   0.0387   1.0000
  15.500   1.2240   0.08719   0.07993  -0.0128   0.0380   1.0000
  15.750   1.2339   0.08939   0.08227  -0.0120   0.0376   1.0000
  16.000   1.2399   0.09234   0.08540  -0.0117   0.0374   1.0000
  16.250   1.2411   0.09608   0.08935  -0.0121   0.0373   1.0000
  16.500   1.2365   0.10073   0.09423  -0.0134   0.0375   1.0000
  16.750   1.2261   0.10641   0.10016  -0.0157   0.0377   1.0000
  17.000   1.2115   0.11290   0.10689  -0.0188   0.0380   1.0000
  17.250   1.1935   0.12021   0.11445  -0.0229   0.0383   1.0000
  17.500   1.1722   0.12850   0.12297  -0.0279   0.0388   1.0000
  17.750   1.1484   0.13780   0.13249  -0.0338   0.0393   1.0000
  18.000   1.1201   0.14874   0.14362  -0.0410   0.0399   1.0000
  18.250   1.0892   0.16124   0.15622  -0.0492   0.0408   1.0000
  18.500   1.0625   0.17359   0.16863  -0.0568   0.0417   1.0000
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