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GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 442 AIRFOIL (goe442-il)
Reynolds number: 50,000
Max Cl/Cd: 35.34 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe442-il-50000.txt
Download as CSV file: xf-goe442-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 442 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3644   0.10164   0.09498  -0.0185   1.0000   0.1711
  -7.500  -0.3840   0.10190   0.09543  -0.0197   1.0000   0.1728
  -7.250  -0.3623   0.09619   0.08969  -0.0165   1.0000   0.1844
  -7.000  -0.3816   0.09646   0.09014  -0.0195   1.0000   0.1879
  -6.750  -0.3666   0.09160   0.08531  -0.0156   1.0000   0.2006
  -6.250  -0.3734   0.08786   0.08176  -0.0177   1.0000   0.2178
  -6.000  -0.3622   0.08357   0.07753  -0.0135   1.0000   0.2295
  -5.750  -0.3596   0.08064   0.07469  -0.0124   1.0000   0.2399
  -5.500  -0.3591   0.07817   0.07229  -0.0125   1.0000   0.2520
  -5.000  -0.3524   0.07277   0.06703  -0.0103   1.0000   0.2826
  -4.750  -0.3479   0.07009   0.06442  -0.0083   1.0000   0.3017
  -4.500  -0.3454   0.06763   0.06200  -0.0076   1.0000   0.3256
  -4.250  -0.3424   0.06520   0.05964  -0.0053   1.0000   0.3546
  -4.000  -0.3397   0.06246   0.05700  -0.0010   1.0000   0.3858
  -3.750  -0.3375   0.05983   0.05447   0.0040   1.0000   0.4201
  -3.500  -0.3382   0.05739   0.05213   0.0094   1.0000   0.4630
  -3.250  -0.3427   0.05541   0.05025   0.0160   1.0000   0.5180
  -3.000  -0.3459   0.05266   0.04765   0.0245   1.0000   0.5663
  -2.750  -0.3478   0.05007   0.04516   0.0329   1.0000   0.6168
  -2.500  -0.1284   0.03735   0.02958  -0.0420   1.0000   0.1905
  -2.250  -0.0940   0.03410   0.02559  -0.0438   1.0000   0.1718
  -2.000  -0.0674   0.03189   0.02301  -0.0440   1.0000   0.1709
  -1.750  -0.0405   0.02990   0.02062  -0.0441   1.0000   0.1684
  -1.500  -0.0142   0.02853   0.01873  -0.0439   1.0000   0.1725
  -1.250   0.0094   0.02726   0.01732  -0.0435   1.0000   0.1776
  -1.000   0.0317   0.02642   0.01625  -0.0429   1.0000   0.1831
  -0.750   0.0517   0.02588   0.01559  -0.0422   1.0000   0.1939
  -0.500   0.0736   0.02559   0.01503  -0.0418   1.0000   0.2032
  -0.250   0.0940   0.02549   0.01489  -0.0416   1.0000   0.2166
   0.000   0.1206   0.02561   0.01509  -0.0430   0.9966   0.2411
   0.250   0.1884   0.02474   0.01493  -0.0508   0.9776   0.3687
   0.500   0.2607   0.02359   0.01448  -0.0586   0.9561   1.0000
   0.750   0.3200   0.02425   0.01477  -0.0651   0.9298   1.0000
   1.000   0.3732   0.02469   0.01497  -0.0701   0.9043   1.0000
   1.250   0.4302   0.02489   0.01499  -0.0753   0.8824   1.0000
   1.500   0.4770   0.02501   0.01500  -0.0786   0.8593   1.0000
   1.750   0.5333   0.02481   0.01473  -0.0829   0.8408   1.0000
   2.000   0.5715   0.02491   0.01477  -0.0842   0.8191   1.0000
   2.250   0.6144   0.02481   0.01465  -0.0860   0.8001   1.0000
   2.500   0.6571   0.02465   0.01446  -0.0874   0.7825   1.0000
   2.750   0.6906   0.02482   0.01461  -0.0876   0.7635   1.0000
   3.000   0.7208   0.02512   0.01490  -0.0873   0.7443   1.0000
   3.250   0.7526   0.02535   0.01516  -0.0872   0.7264   1.0000
   3.500   0.7848   0.02553   0.01532  -0.0868   0.7086   1.0000
   3.750   0.8113   0.02576   0.01554  -0.0854   0.6867   1.0000
   4.000   0.8427   0.02547   0.01520  -0.0839   0.6627   1.0000
   4.250   0.8657   0.02567   0.01537  -0.0818   0.6371   1.0000
   4.500   0.8917   0.02585   0.01549  -0.0801   0.6141   1.0000
   4.750   0.9157   0.02629   0.01592  -0.0785   0.5921   1.0000
   5.000   0.9409   0.02672   0.01635  -0.0770   0.5706   1.0000
   5.250   0.9635   0.02730   0.01695  -0.0753   0.5468   1.0000
   5.500   0.9858   0.02795   0.01760  -0.0735   0.5221   1.0000
   5.750   1.0101   0.02858   0.01819  -0.0719   0.4965   1.0000
   6.000   1.0318   0.02934   0.01892  -0.0700   0.4677   1.0000
   6.250   1.0523   0.03014   0.01967  -0.0679   0.4376   1.0000
   6.500   1.0718   0.03104   0.02055  -0.0659   0.4086   1.0000
   6.750   1.0899   0.03229   0.02189  -0.0640   0.3838   1.0000
   7.000   1.1125   0.03345   0.02307  -0.0627   0.3649   1.0000
   7.250   1.1345   0.03474   0.02438  -0.0615   0.3489   1.0000
   7.500   1.1539   0.03619   0.02598  -0.0601   0.3346   1.0000
   7.750   1.1699   0.03804   0.02810  -0.0586   0.3225   1.0000
   8.000   1.1851   0.04027   0.03066  -0.0572   0.3134   1.0000
   8.250   1.2102   0.04168   0.03209  -0.0565   0.3047   1.0000
   8.500   1.2139   0.04467   0.03559  -0.0542   0.2962   1.0000
   8.750   1.2335   0.04651   0.03756  -0.0531   0.2882   1.0000
   9.000   1.2319   0.05022   0.04175  -0.0508   0.2822   1.0000
   9.250   1.2518   0.05196   0.04362  -0.0497   0.2737   1.0000
   9.500   1.2377   0.05651   0.04864  -0.0470   0.2681   1.0000
   9.750   1.2532   0.05828   0.05055  -0.0454   0.2582   1.0000
  10.000   1.2214   0.06446   0.05706  -0.0429   0.2561   1.0000
  10.250   1.1407   0.07583   0.06844  -0.0419   0.2640   1.0000
  10.500   1.1190   0.08223   0.07486  -0.0423   0.2619   1.0000
  11.500   1.2252   0.07538   0.06864  -0.0286   0.1802   1.0000
  11.750   1.1989   0.08133   0.07466  -0.0286   0.1783   1.0000
  12.000   1.1734   0.08840   0.08176  -0.0302   0.1768   1.0000
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