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GOE 400 AIRFOIL (goe400-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 400 AIRFOIL (goe400-il)
Reynolds number: 50,000
Max Cl/Cd: 41.89 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe400-il-50000-n5.txt
Download as CSV file: xf-goe400-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 400 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3714   0.10724   0.10051  -0.0076   1.0000   0.0926
  -7.750  -0.3698   0.10572   0.09909  -0.0110   1.0000   0.0938
  -7.500  -0.3634   0.10386   0.09728  -0.0163   1.0000   0.0943
  -7.250  -0.3530   0.09925   0.09273  -0.0167   1.0000   0.0952
  -7.000  -0.3410   0.09451   0.08801  -0.0141   1.0000   0.0989
  -6.750  -0.3308   0.09161   0.08515  -0.0163   1.0000   0.1029
  -6.500  -0.3187   0.08956   0.08314  -0.0226   1.0000   0.1062
  -6.250  -0.3025   0.08730   0.08087  -0.0297   1.0000   0.1071
  -6.000  -0.2884   0.08365   0.07724  -0.0325   1.0000   0.1076
  -5.750  -0.2797   0.07925   0.07291  -0.0304   1.0000   0.1088
  -5.500  -0.2697   0.07590   0.06961  -0.0293   1.0000   0.1119
  -5.250  -0.2554   0.07338   0.06711  -0.0320   1.0000   0.1182
  -4.750  -0.2242   0.06794   0.06166  -0.0389   1.0000   0.1223
  -4.500  -0.2166   0.06513   0.05890  -0.0381   1.0000   0.1233
  -4.250  -0.2082   0.06274   0.05652  -0.0382   1.0000   0.1241
  -4.000  -0.1628   0.05694   0.05038  -0.0470   0.9905   0.0915
  -3.750  -0.1163   0.05277   0.04596  -0.0549   0.9778   0.0915
  -3.500  -0.0706   0.04877   0.04171  -0.0618   0.9655   0.0897
  -3.000   0.0286   0.04026   0.03227  -0.0761   0.9417   0.0821
  -2.750   0.0714   0.03719   0.02883  -0.0806   0.9294   0.0819
  -2.500   0.1137   0.03439   0.02561  -0.0845   0.9172   0.0834
  -2.250   0.1492   0.03306   0.02416  -0.0867   0.9038   0.0884
  -2.000   0.1869   0.03099   0.02164  -0.0890   0.8900   0.0914
  -1.750   0.2234   0.02896   0.01911  -0.0908   0.8765   0.0930
  -1.500   0.2576   0.02729   0.01701  -0.0919   0.8630   0.0955
  -1.250   0.2890   0.02620   0.01571  -0.0924   0.8494   0.0992
  -1.000   0.3210   0.02504   0.01410  -0.0928   0.8362   0.1057
  -0.750   0.3500   0.02439   0.01332  -0.0928   0.8229   0.1175
  -0.500   0.3791   0.02369   0.01238  -0.0925   0.8101   0.1316
  -0.250   0.4094   0.02310   0.01148  -0.0923   0.7979   0.1507
   0.000   0.4371   0.02274   0.01111  -0.0920   0.7852   0.1727
   0.250   0.4645   0.02250   0.01072  -0.0915   0.7722   0.1945
   0.500   0.4915   0.02222   0.01036  -0.0909   0.7595   0.2073
   0.750   0.5181   0.02202   0.01010  -0.0902   0.7473   0.2188
   1.000   0.5445   0.02187   0.00988  -0.0895   0.7355   0.2285
   1.250   0.5709   0.02177   0.00971  -0.0887   0.7242   0.2368
   1.500   0.5965   0.02174   0.00971  -0.0880   0.7115   0.2463
   1.750   0.6221   0.02173   0.00978  -0.0874   0.6994   0.2618
   2.000   0.6482   0.02167   0.00986  -0.0868   0.6878   0.2901
   2.250   0.6747   0.02035   0.00987  -0.0862   0.6771   1.0000
   2.500   0.7009   0.02070   0.01001  -0.0855   0.6649   1.0000
   2.750   0.7266   0.02107   0.01027  -0.0849   0.6525   1.0000
   3.000   0.7523   0.02143   0.01053  -0.0842   0.6406   1.0000
   3.250   0.7781   0.02177   0.01079  -0.0834   0.6293   1.0000
   3.500   0.8038   0.02210   0.01107  -0.0827   0.6180   1.0000
   3.750   0.8288   0.02252   0.01150  -0.0820   0.6053   1.0000
   4.000   0.8537   0.02293   0.01194  -0.0813   0.5928   1.0000
   4.250   0.8787   0.02333   0.01239  -0.0806   0.5806   1.0000
   4.500   0.9039   0.02370   0.01278  -0.0798   0.5688   1.0000
   4.750   0.9292   0.02402   0.01312  -0.0789   0.5572   1.0000
   5.000   0.9535   0.02447   0.01367  -0.0782   0.5437   1.0000
   5.250   0.9777   0.02491   0.01424  -0.0774   0.5302   1.0000
   5.500   1.0017   0.02530   0.01473  -0.0765   0.5160   1.0000
   5.750   1.0256   0.02563   0.01516  -0.0755   0.5010   1.0000
   6.000   1.0492   0.02594   0.01559  -0.0744   0.4852   1.0000
   6.250   1.0727   0.02621   0.01596  -0.0732   0.4688   1.0000
   6.500   1.0953   0.02653   0.01638  -0.0720   0.4505   1.0000
   6.750   1.1170   0.02691   0.01691  -0.0708   0.4301   1.0000
   7.000   1.1389   0.02720   0.01731  -0.0694   0.4095   1.0000
   7.250   1.1598   0.02769   0.01795  -0.0682   0.3884   1.0000
   7.500   1.1806   0.02826   0.01868  -0.0670   0.3682   1.0000
   7.750   1.2012   0.02885   0.01940  -0.0657   0.3488   1.0000
   8.000   1.2203   0.02966   0.02043  -0.0644   0.3267   1.0000
   8.250   1.2385   0.03046   0.02137  -0.0629   0.3035   1.0000
   8.500   1.2532   0.03147   0.02247  -0.0613   0.2734   1.0000
   8.750   1.2615   0.03276   0.02363  -0.0594   0.2311   1.0000
   9.000   1.2654   0.03460   0.02522  -0.0576   0.1848   1.0000
   9.250   1.2683   0.03680   0.02722  -0.0559   0.1496   1.0000
   9.500   1.2693   0.03925   0.02958  -0.0542   0.1231   1.0000
   9.750   1.2648   0.04204   0.03224  -0.0523   0.1041   1.0000
  10.000   1.2582   0.04523   0.03535  -0.0507   0.0909   1.0000
  10.250   1.2514   0.04870   0.03882  -0.0497   0.0807   1.0000
  10.500   1.2477   0.05211   0.04235  -0.0489   0.0711   1.0000
  10.750   1.2433   0.05566   0.04590  -0.0485   0.0648   1.0000
  11.000   1.2432   0.05889   0.04941  -0.0480   0.0585   1.0000
  11.250   1.2411   0.06229   0.05287  -0.0478   0.0550   1.0000
  11.500   1.2426   0.06543   0.05617  -0.0470   0.0518   1.0000
  11.750   1.2437   0.06867   0.05961  -0.0465   0.0487   1.0000
  12.000   1.2427   0.07215   0.06320  -0.0466   0.0462   1.0000
  12.250   1.2407   0.07569   0.06675  -0.0468   0.0443   1.0000
  12.500   1.2409   0.07941   0.07075  -0.0465   0.0424   1.0000
  12.750   1.2395   0.08345   0.07506  -0.0466   0.0410   1.0000
  13.000   1.2361   0.08788   0.07974  -0.0471   0.0400   1.0000
  13.250   1.2299   0.09284   0.08495  -0.0481   0.0393   1.0000
  13.500   1.2207   0.09842   0.09077  -0.0499   0.0389   1.0000
  13.750   1.2086   0.10471   0.09730  -0.0524   0.0386   1.0000
  14.000   1.1934   0.11192   0.10474  -0.0559   0.0385   1.0000
  14.250   1.1743   0.12049   0.11355  -0.0605   0.0388   1.0000
  14.500   1.1517   0.13080   0.12407  -0.0666   0.0394   1.0000
  14.750   1.1256   0.14328   0.13669  -0.0742   0.0403   1.0000
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