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GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 604 AIRFOIL (goe604-il)
Reynolds number: 200,000
Max Cl/Cd: 59.23 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe604-il-200000.txt
Download as CSV file: xf-goe604-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 604 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5191   0.05571   0.05198  -0.0868   0.9899   0.0548
 -11.000  -0.5364   0.04900   0.04488  -0.0931   0.9733   0.0546
 -10.750  -0.5439   0.04318   0.03843  -0.0968   0.9578   0.0550
 -10.500  -0.5238   0.03898   0.03398  -0.0998   0.9491   0.0560
 -10.250  -0.4854   0.03747   0.03257  -0.1025   0.9397   0.0575
 -10.000  -0.4669   0.03464   0.02941  -0.1034   0.9244   0.0583
  -9.750  -0.4485   0.03221   0.02663  -0.1035   0.9067   0.0594
  -9.500  -0.4309   0.03018   0.02418  -0.1029   0.8865   0.0607
  -9.250  -0.4150   0.02867   0.02216  -0.1013   0.8643   0.0619
  -9.000  -0.3957   0.02678   0.02009  -0.1003   0.8404   0.0630
  -8.750  -0.3734   0.02559   0.01876  -0.0994   0.8175   0.0643
  -8.500  -0.3516   0.02469   0.01767  -0.0983   0.7961   0.0659
  -8.250  -0.3308   0.02384   0.01654  -0.0970   0.7764   0.0676
  -8.000  -0.3103   0.02311   0.01547  -0.0955   0.7586   0.0692
  -7.750  -0.2882   0.02200   0.01420  -0.0945   0.7428   0.0708
  -7.500  -0.2647   0.02122   0.01336  -0.0937   0.7288   0.0726
  -7.250  -0.2413   0.02065   0.01265  -0.0927   0.7165   0.0750
  -7.000  -0.2182   0.02013   0.01194  -0.0917   0.7041   0.0775
  -6.750  -0.1950   0.01935   0.01110  -0.0908   0.6934   0.0800
  -6.500  -0.1715   0.01882   0.01053  -0.0899   0.6834   0.0830
  -6.250  -0.1480   0.01839   0.01000  -0.0889   0.6735   0.0866
  -6.000  -0.1253   0.01783   0.00941  -0.0879   0.6646   0.0910
  -5.750  -0.1018   0.01747   0.00902  -0.0869   0.6557   0.0966
  -5.500  -0.0789   0.01704   0.00859  -0.0859   0.6474   0.1033
  -5.250  -0.0551   0.01675   0.00829  -0.0850   0.6398   0.1136
  -5.000  -0.0311   0.01651   0.00810  -0.0841   0.6319   0.1297
  -4.750  -0.0063   0.01633   0.00788  -0.0833   0.6253   0.1543
  -4.500   0.0174   0.01619   0.00779  -0.0824   0.6178   0.1778
  -4.250   0.0423   0.01611   0.00766  -0.0817   0.6108   0.1959
  -4.000   0.0679   0.01607   0.00757  -0.0812   0.6047   0.2107
  -3.750   0.0925   0.01598   0.00750  -0.0804   0.5976   0.2237
  -3.500   0.1186   0.01596   0.00738  -0.0799   0.5914   0.2363
  -3.250   0.1444   0.01593   0.00733  -0.0794   0.5854   0.2488
  -3.000   0.1690   0.01581   0.00726  -0.0787   0.5785   0.2610
  -2.750   0.1951   0.01574   0.00714  -0.0781   0.5724   0.2749
  -2.500   0.2209   0.01574   0.00710  -0.0776   0.5667   0.2914
  -2.250   0.2451   0.01563   0.00709  -0.0768   0.5601   0.3111
  -2.000   0.2702   0.01549   0.00700  -0.0761   0.5544   0.3336
  -1.750   0.2954   0.01539   0.00695  -0.0755   0.5492   0.3606
  -1.500   0.3182   0.01519   0.00692  -0.0745   0.5425   0.3930
  -1.250   0.3418   0.01498   0.00683  -0.0735   0.5366   0.4335
  -1.000   0.3654   0.01482   0.00680  -0.0726   0.5314   0.4867
  -0.750   0.3844   0.01452   0.00687  -0.0707   0.5249   0.5610
  -0.500   0.4035   0.01416   0.00693  -0.0686   0.5193   0.6737
  -0.250   0.4355   0.01399   0.00710  -0.0684   0.5143   0.8182
   0.000   0.4954   0.01417   0.00741  -0.0741   0.5062   0.9062
   0.250   0.5491   0.01440   0.00749  -0.0787   0.4996   0.9410
   0.500   0.5979   0.01469   0.00765  -0.0826   0.4932   0.9629
   0.750   0.6487   0.01488   0.00775  -0.0871   0.4858   0.9794
   1.000   0.7063   0.01503   0.00768  -0.0930   0.4795   0.9919
   1.250   0.7532   0.01513   0.00775  -0.0971   0.4725   1.0000
   1.500   0.7718   0.01525   0.00780  -0.0956   0.4673   1.0000
   1.750   0.7923   0.01539   0.00782  -0.0943   0.4630   1.0000
   2.000   0.8121   0.01561   0.00798  -0.0929   0.4585   1.0000
   2.250   0.8301   0.01579   0.00817  -0.0912   0.4534   1.0000
   2.500   0.8503   0.01597   0.00828  -0.0899   0.4490   1.0000
   2.750   0.8724   0.01617   0.00837  -0.0889   0.4452   1.0000
   3.000   0.8927   0.01645   0.00861  -0.0876   0.4412   1.0000
   3.250   0.9110   0.01668   0.00886  -0.0859   0.4365   1.0000
   3.500   0.9316   0.01686   0.00899  -0.0846   0.4320   1.0000
   3.750   0.9544   0.01704   0.00905  -0.0837   0.4280   1.0000
   4.000   0.9741   0.01731   0.00932  -0.0823   0.4236   1.0000
   4.250   0.9926   0.01756   0.00959  -0.0806   0.4193   1.0000
   4.500   1.0137   0.01778   0.00977  -0.0794   0.4153   1.0000
   4.750   1.0367   0.01800   0.00992  -0.0786   0.4119   1.0000
   5.000   1.0604   0.01834   0.01018  -0.0780   0.4086   1.0000
   5.250   1.0772   0.01865   0.01057  -0.0761   0.4049   1.0000
   5.500   1.0968   0.01894   0.01089  -0.0747   0.4013   1.0000
   5.750   1.1186   0.01920   0.01113  -0.0737   0.3981   1.0000
   6.000   1.1424   0.01947   0.01133  -0.0731   0.3951   1.0000
   6.250   1.1673   0.01986   0.01166  -0.0727   0.3921   1.0000
   6.500   1.1816   0.02020   0.01211  -0.0705   0.3885   1.0000
   6.750   1.1995   0.02050   0.01246  -0.0689   0.3849   1.0000
   7.000   1.2205   0.02075   0.01269  -0.0678   0.3814   1.0000
   7.250   1.2444   0.02102   0.01291  -0.0673   0.3785   1.0000
   7.500   1.2711   0.02146   0.01328  -0.0673   0.3758   1.0000
   7.750   1.2834   0.02188   0.01384  -0.0649   0.3729   1.0000
   8.000   1.2982   0.02225   0.01430  -0.0629   0.3693   1.0000
   8.250   1.3168   0.02253   0.01460  -0.0615   0.3659   1.0000
   8.500   1.3395   0.02282   0.01485  -0.0608   0.3629   1.0000
   8.750   1.3674   0.02320   0.01516  -0.0611   0.3601   1.0000
   9.000   1.3787   0.02371   0.01580  -0.0587   0.3572   1.0000
   9.250   1.3888   0.02419   0.01639  -0.0561   0.3540   1.0000
   9.500   1.4030   0.02456   0.01683  -0.0541   0.3506   1.0000
   9.750   1.4225   0.02484   0.01710  -0.0530   0.3473   1.0000
  10.000   1.4508   0.02513   0.01730  -0.0534   0.3440   1.0000
  10.250   1.4542   0.02569   0.01798  -0.0497   0.3408   1.0000
  10.500   1.4543   0.02625   0.01867  -0.0456   0.3374   1.0000
  10.750   1.4637   0.02669   0.01918  -0.0432   0.3338   1.0000
  11.000   1.4826   0.02698   0.01944  -0.0421   0.3303   1.0000
  11.250   1.5095   0.02733   0.01973  -0.0424   0.3266   1.0000
  11.500   1.4989   0.02826   0.02087  -0.0375   0.3231   1.0000
  11.750   1.5001   0.02905   0.02177  -0.0345   0.3190   1.0000
  12.000   1.5136   0.02949   0.02221  -0.0330   0.3149   1.0000
  12.250   1.5411   0.02970   0.02232  -0.0333   0.3107   1.0000
  12.500   1.5225   0.03129   0.02415  -0.0287   0.3064   1.0000
  12.750   1.5223   0.03240   0.02535  -0.0263   0.3015   1.0000
  13.000   1.5396   0.03278   0.02567  -0.0255   0.2969   1.0000
  13.250   1.5327   0.03446   0.02749  -0.0231   0.2917   1.0000
  13.500   1.5246   0.03632   0.02947  -0.0209   0.2859   1.0000
  13.750   1.5417   0.03678   0.02985  -0.0203   0.2808   1.0000
  14.000   1.5232   0.03970   0.03296  -0.0183   0.2746   1.0000
  14.250   1.5200   0.04169   0.03499  -0.0172   0.2684   1.0000
  14.500   1.5289   0.04289   0.03615  -0.0165   0.2630   1.0000
  14.750   1.5077   0.04673   0.04016  -0.0155   0.2564   1.0000
  15.000   1.5173   0.04794   0.04132  -0.0151   0.2513   1.0000
  15.250   1.5043   0.05145   0.04494  -0.0147   0.2455   1.0000
  15.500   1.4967   0.05458   0.04815  -0.0145   0.2403   1.0000
  15.750   1.5131   0.05518   0.04866  -0.0142   0.2359   1.0000
  16.000   1.4953   0.05962   0.05326  -0.0143   0.2313   1.0000
  16.250   1.4865   0.06316   0.05689  -0.0145   0.2269   1.0000
  16.500   1.4964   0.06456   0.05827  -0.0144   0.2233   1.0000
  16.750   1.5043   0.06623   0.05994  -0.0143   0.2200   1.0000
  17.000   1.4831   0.07151   0.06541  -0.0149   0.2166   1.0000
  17.250   1.4749   0.07527   0.06927  -0.0155   0.2132   1.0000
  17.500   1.4826   0.07703   0.07105  -0.0156   0.2104   1.0000
  17.750   1.5151   0.07561   0.06951  -0.0149   0.2075   1.0000
  18.000   1.4830   0.08255   0.07669  -0.0163   0.2050   1.0000
  18.250   1.4473   0.09024   0.08460  -0.0180   0.2023   1.0000
  18.500   1.4243   0.09636   0.09086  -0.0195   0.1993   1.0000
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