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GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 457 AIRFOIL (goe457-il)
Reynolds number: 50,000
Max Cl/Cd: 40.12 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe457-il-50000-n5.txt
Download as CSV file: xf-goe457-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 457 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3496   0.09873   0.09217  -0.0226   1.0000   0.1019
  -7.250  -0.3594   0.09727   0.09086  -0.0229   1.0000   0.1044
  -7.000  -0.3677   0.09585   0.08955  -0.0262   1.0000   0.1059
  -6.750  -0.3693   0.09361   0.08736  -0.0300   1.0000   0.1064
  -6.500  -0.3589   0.08859   0.08242  -0.0230   1.0000   0.1096
  -6.250  -0.3553   0.08591   0.07979  -0.0221   1.0000   0.1151
  -6.000  -0.3552   0.08411   0.07798  -0.0301   1.0000   0.1209
  -5.750  -0.3503   0.08010   0.07409  -0.0248   1.0000   0.1243
  -5.500  -0.3439   0.07717   0.07118  -0.0244   1.0000   0.1284
  -5.000  -0.3085   0.06563   0.05932  -0.0357   1.0000   0.0740
  -4.750  -0.2947   0.06181   0.05543  -0.0371   1.0000   0.0717
  -4.500  -0.2762   0.05783   0.05131  -0.0397   1.0000   0.0718
  -4.250  -0.2553   0.05379   0.04708  -0.0423   1.0000   0.0719
  -4.000  -0.2325   0.04966   0.04269  -0.0447   1.0000   0.0702
  -3.750  -0.2069   0.04551   0.03820  -0.0472   1.0000   0.0688
  -3.500  -0.1819   0.04231   0.03466  -0.0489   1.0000   0.0712
  -3.250  -0.1548   0.03914   0.03103  -0.0505   1.0000   0.0733
  -3.000  -0.1281   0.03628   0.02769  -0.0515   1.0000   0.0734
  -2.750  -0.1014   0.03383   0.02475  -0.0521   1.0000   0.0738
  -2.500  -0.0743   0.03195   0.02225  -0.0524   1.0000   0.0761
  -2.250  -0.0328   0.03018   0.02027  -0.0559   0.9916   0.0807
  -2.000   0.0103   0.02854   0.01819  -0.0589   0.9828   0.0826
  -1.750   0.0535   0.02719   0.01642  -0.0618   0.9732   0.0849
  -1.500   0.0954   0.02608   0.01496  -0.0643   0.9624   0.0881
  -1.250   0.1376   0.02514   0.01380  -0.0668   0.9512   0.0941
  -1.000   0.1806   0.02442   0.01286  -0.0695   0.9389   0.1051
  -0.750   0.2215   0.02358   0.01198  -0.0717   0.9253   0.1149
  -0.500   0.2625   0.02278   0.01116  -0.0738   0.9110   0.1337
  -0.250   0.3033   0.02179   0.01062  -0.0761   0.8961   0.2063
   0.000   0.3459   0.01926   0.01014  -0.0784   0.8817   1.0000
   0.250   0.3847   0.01915   0.00965  -0.0798   0.8627   1.0000
   0.500   0.4186   0.01906   0.00930  -0.0804   0.8396   1.0000
   0.750   0.4516   0.01895   0.00899  -0.0807   0.8150   1.0000
   1.000   0.4871   0.01881   0.00865  -0.0814   0.7906   1.0000
   1.250   0.5231   0.01869   0.00833  -0.0821   0.7651   1.0000
   1.500   0.5595   0.01861   0.00805  -0.0829   0.7393   1.0000
   1.750   0.5955   0.01860   0.00781  -0.0836   0.7141   1.0000
   2.000   0.6291   0.01870   0.00768  -0.0840   0.6892   1.0000
   2.250   0.6586   0.01895   0.00774  -0.0838   0.6645   1.0000
   2.500   0.6883   0.01925   0.00784  -0.0836   0.6426   1.0000
   2.750   0.7154   0.01962   0.00808  -0.0832   0.6214   1.0000
   3.000   0.7427   0.02002   0.00836  -0.0828   0.6025   1.0000
   3.250   0.7699   0.02044   0.00866  -0.0824   0.5852   1.0000
   3.500   0.7970   0.02089   0.00902  -0.0821   0.5692   1.0000
   3.750   0.8237   0.02137   0.00946  -0.0817   0.5539   1.0000
   4.000   0.8502   0.02187   0.00994  -0.0813   0.5393   1.0000
   4.250   0.8763   0.02240   0.01047  -0.0810   0.5253   1.0000
   4.500   0.9020   0.02295   0.01108  -0.0805   0.5117   1.0000
   4.750   0.9275   0.02353   0.01171  -0.0800   0.4988   1.0000
   5.000   0.9527   0.02412   0.01237  -0.0795   0.4863   1.0000
   5.250   0.9777   0.02471   0.01305  -0.0789   0.4738   1.0000
   5.500   1.0013   0.02527   0.01368  -0.0780   0.4597   1.0000
   5.750   1.0222   0.02575   0.01424  -0.0767   0.4421   1.0000
   6.000   1.0419   0.02616   0.01471  -0.0751   0.4229   1.0000
   6.250   1.0614   0.02651   0.01512  -0.0734   0.4037   1.0000
   6.500   1.0811   0.02695   0.01563  -0.0719   0.3863   1.0000
   6.750   1.1000   0.02745   0.01628  -0.0703   0.3685   1.0000
   7.000   1.1182   0.02795   0.01690  -0.0686   0.3498   1.0000
   7.250   1.1360   0.02846   0.01754  -0.0669   0.3309   1.0000
   7.500   1.1528   0.02904   0.01822  -0.0651   0.3108   1.0000
   7.750   1.1687   0.02972   0.01902  -0.0632   0.2892   1.0000
   8.000   1.1840   0.03048   0.01982  -0.0613   0.2688   1.0000
   8.250   1.1983   0.03142   0.02087  -0.0593   0.2465   1.0000
   8.500   1.2116   0.03246   0.02196  -0.0573   0.2270   1.0000
   8.750   1.2244   0.03362   0.02311  -0.0553   0.2103   1.0000
   9.000   1.2372   0.03487   0.02444  -0.0534   0.1961   1.0000
   9.250   1.2509   0.03622   0.02592  -0.0516   0.1845   1.0000
   9.500   1.2642   0.03760   0.02745  -0.0499   0.1752   1.0000
   9.750   1.2726   0.03890   0.02881  -0.0477   0.1647   1.0000
  10.000   1.2760   0.04020   0.03012  -0.0451   0.1541   1.0000
  10.500   1.2826   0.04331   0.03359  -0.0404   0.1364   1.0000
  10.750   1.2855   0.04506   0.03547  -0.0383   0.1299   1.0000
  11.000   1.2875   0.04701   0.03759  -0.0364   0.1240   1.0000
  11.250   1.2878   0.04915   0.03995  -0.0347   0.1178   1.0000
  11.500   1.2840   0.05161   0.04248  -0.0332   0.1116   1.0000
  11.750   1.2778   0.05456   0.04568  -0.0323   0.1041   1.0000
  12.000   1.2705   0.05777   0.04894  -0.0318   0.0982   1.0000
  12.250   1.2643   0.06141   0.05294  -0.0319   0.0920   1.0000
  12.500   1.2559   0.06536   0.05698  -0.0325   0.0866   1.0000
  12.750   1.2457   0.07011   0.06202  -0.0340   0.0798   1.0000
  13.000   1.2352   0.07498   0.06700  -0.0358   0.0743   1.0000
  13.250   1.2253   0.08024   0.07252  -0.0376   0.0690   1.0000
  13.500   1.2146   0.08570   0.07818  -0.0397   0.0641   1.0000
  13.750   1.2043   0.09102   0.08352  -0.0418   0.0605   1.0000
  14.000   1.1920   0.09733   0.09011  -0.0443   0.0566   1.0000
  14.250   1.1795   0.10371   0.09668  -0.0470   0.0534   1.0000
  14.500   1.1684   0.10985   0.10290  -0.0498   0.0505   1.0000
  14.750   1.1593   0.11560   0.10865  -0.0524   0.0481   1.0000
  15.000   1.1438   0.12353   0.11681  -0.0563   0.0470   1.0000
  15.250   1.1256   0.13255   0.12600  -0.0609   0.0464   1.0000
  15.500   1.1044   0.14296   0.13651  -0.0665   0.0465   1.0000
  15.750   1.0824   0.15448   0.14804  -0.0728   0.0466   1.0000
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