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GOE 420 AIRFOIL (goe420-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 420 AIRFOIL (goe420-il)
Reynolds number: 50,000
Max Cl/Cd: 13.4 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe420-il-50000-n5.txt
Download as CSV file: xf-goe420-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 420 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3088   0.13599   0.12847  -0.0479   1.0000   0.0847
 -12.000  -0.3188   0.13341   0.12594  -0.0470   1.0000   0.0842
 -11.750  -0.3294   0.13074   0.12334  -0.0462   1.0000   0.0841
 -11.500  -0.3234   0.12578   0.11838  -0.0501   0.9956   0.0848
 -11.250  -0.3190   0.12038   0.11296  -0.0544   0.9905   0.0855
 -11.000  -0.3182   0.11456   0.10713  -0.0588   0.9851   0.0860
 -10.750  -0.3192   0.10813   0.10069  -0.0637   0.9804   0.0861
 -10.500  -0.3300   0.10063   0.09318  -0.0686   0.9742   0.0861
 -10.250  -0.3642   0.08836   0.08088  -0.0768   0.9682   0.0859
 -10.000  -0.4600   0.06946   0.06161  -0.0908   0.9565   0.0845
  -9.750  -0.5060   0.06212   0.05393  -0.0959   0.9444   0.0841
  -9.500  -0.5218   0.05822   0.04973  -0.0971   0.9348   0.0846
  -9.250  -0.5320   0.05547   0.04674  -0.0961   0.9245   0.0852
  -9.000  -0.5265   0.05251   0.04346  -0.0970   0.9175   0.0866
  -8.750  -0.5280   0.05039   0.04103  -0.0954   0.9085   0.0880
  -8.500  -0.5142   0.04867   0.03917  -0.0953   0.9017   0.0901
  -8.250  -0.4882   0.04728   0.03774  -0.0967   0.8973   0.0929
  -8.000  -0.4872   0.04624   0.03658  -0.0938   0.8878   0.0948
  -7.750  -0.4696   0.04459   0.03462  -0.0938   0.8819   0.0982
  -7.500  -0.4411   0.04342   0.03347  -0.0950   0.8781   0.1014
  -7.250  -0.4403   0.04279   0.03278  -0.0915   0.8683   0.1038
  -7.000  -0.4192   0.04160   0.03139  -0.0914   0.8627   0.1091
  -6.750  -0.3909   0.04063   0.03044  -0.0924   0.8589   0.1155
  -6.500  -0.3911   0.04011   0.02979  -0.0886   0.8492   0.1205
  -6.250  -0.3698   0.03928   0.02900  -0.0884   0.8436   0.1286
  -6.000  -0.3408   0.03825   0.02793  -0.0894   0.8397   0.1416
  -5.750  -0.3402   0.03786   0.02753  -0.0857   0.8301   0.1507
  -5.500  -0.3187   0.03704   0.02679  -0.0854   0.8243   0.1684
  -5.250  -0.2878   0.03621   0.02604  -0.0865   0.8203   0.1944
  -5.000  -0.2850   0.03616   0.02607  -0.0830   0.8101   0.2110
  -4.750  -0.2582   0.03592   0.02591  -0.0831   0.8041   0.2388
  -4.500  -0.2214   0.03567   0.02566  -0.0845   0.8002   0.2694
  -4.250  -0.2193   0.03589   0.02585  -0.0808   0.7884   0.2853
  -4.000  -0.1865   0.03575   0.02565  -0.0814   0.7833   0.3116
  -3.750  -0.1734   0.03597   0.02585  -0.0791   0.7743   0.3309
  -3.500  -0.1502   0.03603   0.02587  -0.0783   0.7672   0.3528
  -3.250  -0.1154   0.03579   0.02555  -0.0790   0.7631   0.3745
  -3.000  -0.1084   0.03606   0.02580  -0.0760   0.7527   0.3855
  -2.750  -0.0789   0.03582   0.02542  -0.0761   0.7470   0.4018
  -2.500  -0.0419   0.03541   0.02487  -0.0772   0.7435   0.4187
  -2.250  -0.0382   0.03587   0.02537  -0.0738   0.7320   0.4273
  -2.000  -0.0052   0.03556   0.02493  -0.0743   0.7272   0.4428
  -1.750   0.0121   0.03571   0.02504  -0.0728   0.7190   0.4548
  -1.500   0.0339   0.03572   0.02500  -0.0718   0.7114   0.4675
  -1.250   0.0688   0.03534   0.02452  -0.0725   0.7074   0.4841
  -1.000   0.0770   0.03586   0.02504  -0.0699   0.6966   0.4968
  -0.750   0.1062   0.03566   0.02484  -0.0697   0.6911   0.5142
  -0.500   0.1427   0.03520   0.02435  -0.0703   0.6878   0.5332
  -0.250   0.1463   0.03603   0.02517  -0.0674   0.6755   0.5453
   0.000   0.1798   0.03566   0.02475  -0.0678   0.6712   0.5620
   0.500   0.2179   0.03617   0.02531  -0.0653   0.6550   0.5910
   0.750   0.2526   0.03572   0.02485  -0.0657   0.6515   0.6110
   1.250   0.2855   0.03657   0.02577  -0.0628   0.6350   0.6514
   1.500   0.3205   0.03602   0.02525  -0.0631   0.6319   0.6807
   2.000   0.3475   0.03700   0.02650  -0.0592   0.6152   0.7446
   2.250   0.3851   0.03638   0.02611  -0.0593   0.6125   0.8081
   2.750   0.4448   0.03793   0.02767  -0.0628   0.5959   1.0000
   3.000   0.4825   0.03760   0.02712  -0.0639   0.5932   1.0000
   3.500   0.5000   0.04008   0.02938  -0.0609   0.5761   1.0000
   3.750   0.5345   0.03989   0.02904  -0.0614   0.5733   1.0000
   4.000   0.5182   0.04283   0.03196  -0.0583   0.5597   1.0000
   4.250   0.5513   0.04264   0.03165  -0.0585   0.5567   1.0000
   4.750   0.5654   0.04590   0.03480  -0.0558   0.5403   1.0000
   5.000   0.5995   0.04555   0.03436  -0.0559   0.5378   1.0000
   5.500   0.6119   0.04912   0.03786  -0.0534   0.5213   1.0000
   5.750   0.6469   0.04862   0.03729  -0.0534   0.5191   1.0000
   6.250   0.6584   0.05237   0.04100  -0.0510   0.5025   1.0000
   6.750   0.6711   0.05619   0.04481  -0.0490   0.4863   1.0000
   7.000   0.7047   0.05565   0.04424  -0.0487   0.4838   1.0000
   7.500   0.7140   0.05995   0.04856  -0.0468   0.4673   1.0000
   8.000   0.7230   0.06445   0.05309  -0.0452   0.4510   1.0000
   8.250   0.7536   0.06416   0.05279  -0.0448   0.4482   1.0000
   8.750   0.7578   0.06937   0.05805  -0.0434   0.4314   1.0000
   9.000   0.7882   0.06908   0.05778  -0.0430   0.4290   1.0000
   9.500   0.7888   0.07486   0.06364  -0.0419   0.4118   1.0000
   9.750   0.7671   0.08030   0.06914  -0.0417   0.3996   1.0000
  10.000   0.7863   0.08128   0.07015  -0.0413   0.3950   1.0000
  10.250   0.8147   0.08118   0.07007  -0.0407   0.3923   1.0000
  10.750   0.8099   0.08805   0.07705  -0.0405   0.3754   1.0000
  11.000   0.8386   0.08790   0.07695  -0.0399   0.3731   1.0000
  11.250   0.8065   0.09501   0.08412  -0.0407   0.3598   1.0000
  11.500   0.8323   0.09513   0.08429  -0.0402   0.3565   1.0000
  11.750   0.8105   0.10116   0.09039  -0.0410   0.3454   1.0000
  12.000   0.8303   0.10195   0.09123  -0.0406   0.3407   1.0000
  12.250   0.8567   0.10180   0.09112  -0.0399   0.3373   1.0000
  12.500   0.8372   0.10744   0.09684  -0.0409   0.3252   1.0000
  12.750   0.8687   0.10636   0.09581  -0.0398   0.3218   1.0000
  13.000   0.8505   0.11188   0.10140  -0.0410   0.3095   1.0000
  13.250   0.8819   0.11057   0.10015  -0.0398   0.3056   1.0000
  13.500   0.8663   0.11586   0.10551  -0.0411   0.2935   1.0000
  13.750   0.8965   0.11454   0.10423  -0.0399   0.2895   1.0000
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