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GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 517 AIRFOIL (goe517-il)
Reynolds number: 100,000
Max Cl/Cd: 55.1 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe517-il-100000.txt
Download as CSV file: xf-goe517-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3633   0.10445   0.09954  -0.0269   1.0000   0.0658
  -8.250  -0.3717   0.10345   0.09867  -0.0288   1.0000   0.0662
  -8.000  -0.3795   0.10245   0.09776  -0.0325   1.0000   0.0665
  -7.750  -0.3501   0.09348   0.08873  -0.0257   1.0000   0.0700
  -7.500  -0.3485   0.09089   0.08620  -0.0251   1.0000   0.0721
  -7.250  -0.3513   0.08863   0.08403  -0.0246   1.0000   0.0739
  -7.000  -0.3523   0.08628   0.08175  -0.0253   1.0000   0.0759
  -6.750  -0.3542   0.08426   0.07980  -0.0275   1.0000   0.0782
  -6.500  -0.3563   0.08369   0.07924  -0.0335   1.0000   0.0798
  -6.250  -0.3551   0.08228   0.07777  -0.0364   1.0000   0.0802
  -6.000  -0.3557   0.07636   0.07203  -0.0305   1.0000   0.0815
  -5.750  -0.3551   0.07348   0.06921  -0.0272   1.0000   0.0829
  -5.500  -0.3543   0.07110   0.06686  -0.0252   1.0000   0.0849
  -5.250  -0.3519   0.06873   0.06450  -0.0245   1.0000   0.0878
  -5.000  -0.3436   0.06652   0.06221  -0.0263   1.0000   0.0922
  -4.750  -0.3293   0.06378   0.05924  -0.0305   1.0000   0.0952
  -4.500  -0.3264   0.06034   0.05589  -0.0277   1.0000   0.0967
  -4.250  -0.3192   0.05774   0.05330  -0.0262   1.0000   0.0996
  -4.000  -0.2941   0.05582   0.05098  -0.0305   1.0000   0.1095
  -3.750  -0.2899   0.05229   0.04762  -0.0279   1.0000   0.1121
  -3.500  -0.2660   0.05089   0.04583  -0.0302   1.0000   0.1239
  -3.250  -0.2419   0.04650   0.04159  -0.0316   0.9956   0.1282
  -3.000  -0.1994   0.04313   0.03793  -0.0367   0.9884   0.1415
  -2.750  -0.1582   0.04008   0.03467  -0.0410   0.9814   0.1568
  -2.500  -0.1195   0.03749   0.03189  -0.0446   0.9731   0.1848
  -2.250  -0.0568   0.03061   0.02357  -0.0488   0.9687   0.0964
  -2.000  -0.0168   0.02755   0.02002  -0.0507   0.9607   0.0891
  -1.750   0.0273   0.02565   0.01737  -0.0529   0.9533   0.0941
  -1.500   0.0679   0.02361   0.01514  -0.0554   0.9449   0.1002
  -1.250   0.1079   0.02241   0.01369  -0.0575   0.9354   0.1148
  -1.000   0.1558   0.02131   0.01231  -0.0608   0.9283   0.1378
  -0.750   0.1938   0.02031   0.01138  -0.0627   0.9171   0.1640
  -0.500   0.2376   0.01944   0.01053  -0.0654   0.9065   0.1957
  -0.250   0.2934   0.01815   0.00948  -0.0701   0.8992   0.2346
   0.000   0.3834   0.01491   0.00825  -0.0816   0.8943   1.0000
   0.250   0.4273   0.01464   0.00764  -0.0838   0.8821   1.0000
   0.500   0.4655   0.01444   0.00724  -0.0850   0.8690   1.0000
   0.750   0.4972   0.01434   0.00700  -0.0850   0.8538   1.0000
   1.000   0.5257   0.01430   0.00684  -0.0845   0.8378   1.0000
   1.250   0.5526   0.01430   0.00675  -0.0836   0.8213   1.0000
   1.500   0.5785   0.01433   0.00668  -0.0825   0.8049   1.0000
   1.750   0.6039   0.01438   0.00664  -0.0814   0.7885   1.0000
   2.000   0.6289   0.01444   0.00662  -0.0802   0.7721   1.0000
   2.250   0.6537   0.01450   0.00663  -0.0790   0.7559   1.0000
   2.500   0.6785   0.01456   0.00661  -0.0778   0.7396   1.0000
   2.750   0.7019   0.01467   0.00667  -0.0764   0.7219   1.0000
   3.000   0.7254   0.01477   0.00674  -0.0751   0.7036   1.0000
   3.250   0.7496   0.01486   0.00677  -0.0738   0.6854   1.0000
   3.500   0.7745   0.01494   0.00680  -0.0726   0.6672   1.0000
   3.750   0.7973   0.01512   0.00696  -0.0713   0.6458   1.0000
   4.000   0.8217   0.01529   0.00704  -0.0701   0.6252   1.0000
   4.500   0.8691   0.01589   0.00751  -0.0677   0.5809   1.0000
   4.750   0.8916   0.01633   0.00792  -0.0664   0.5575   1.0000
   5.000   0.9160   0.01683   0.00830  -0.0655   0.5374   1.0000
   5.250   0.9383   0.01737   0.00888  -0.0643   0.5163   1.0000
   5.500   0.9616   0.01792   0.00946  -0.0633   0.4981   1.0000
   5.750   0.9851   0.01847   0.01003  -0.0624   0.4817   1.0000
   6.000   1.0084   0.01896   0.01055  -0.0614   0.4657   1.0000
   6.250   1.0309   0.01935   0.01098  -0.0603   0.4489   1.0000
   6.500   1.0517   0.01967   0.01146  -0.0589   0.4305   1.0000
   6.750   1.0721   0.01983   0.01166  -0.0573   0.4100   1.0000
   7.000   1.0898   0.01988   0.01174  -0.0552   0.3842   1.0000
   7.250   1.1065   0.02008   0.01193  -0.0531   0.3568   1.0000
   7.500   1.1235   0.02046   0.01238  -0.0512   0.3311   1.0000
   7.750   1.1383   0.02088   0.01288  -0.0489   0.2996   1.0000
   8.000   1.1456   0.02144   0.01340  -0.0455   0.2279   1.0000
   8.250   1.1365   0.02441   0.01521  -0.0406   0.1055   1.0000
   8.500   1.1381   0.02668   0.01730  -0.0368   0.0858   1.0000
   8.750   1.1412   0.02873   0.01927  -0.0335   0.0754   1.0000
   9.000   1.1502   0.03037   0.02098  -0.0309   0.0677   1.0000
   9.250   1.1626   0.03273   0.02323  -0.0288   0.0628   1.0000
   9.500   1.1832   0.03467   0.02534  -0.0275   0.0586   1.0000
   9.750   1.2057   0.03721   0.02778  -0.0272   0.0533   1.0000
  10.000   1.2325   0.04044   0.03121  -0.0271   0.0508   1.0000
  10.250   1.2520   0.04325   0.03437  -0.0258   0.0496   1.0000
  10.500   1.2662   0.04631   0.03782  -0.0241   0.0488   1.0000
  10.750   1.2732   0.04923   0.04113  -0.0218   0.0477   1.0000
  11.000   1.2761   0.05206   0.04430  -0.0193   0.0465   1.0000
  11.250   1.2749   0.05507   0.04767  -0.0166   0.0457   1.0000
  11.500   1.2674   0.05809   0.05101  -0.0134   0.0455   1.0000
  11.750   1.2536   0.06141   0.05465  -0.0102   0.0459   1.0000
  12.000   1.2371   0.06499   0.05853  -0.0077   0.0463   1.0000
  12.250   1.2182   0.06897   0.06279  -0.0061   0.0469   1.0000
  12.500   1.1977   0.07332   0.06740  -0.0055   0.0473   1.0000
  12.750   1.1754   0.07828   0.07258  -0.0061   0.0478   1.0000
  13.000   1.1521   0.08382   0.07833  -0.0077   0.0483   1.0000
  13.250   1.1277   0.09010   0.08476  -0.0106   0.0487   1.0000
  13.500   1.1024   0.09728   0.09209  -0.0145   0.0493   1.0000
  13.750   1.0779   0.10517   0.10011  -0.0193   0.0499   1.0000
  14.000   1.0560   0.11358   0.10860  -0.0242   0.0508   1.0000
  14.250   1.0386   0.12205   0.11710  -0.0287   0.0516   1.0000
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