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GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 534 AIRFOIL (goe534-il)
Reynolds number: 100,000
Max Cl/Cd: 50.17 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe534-il-100000-n5.txt
Download as CSV file: xf-goe534-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 534 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2718   0.09600   0.09066  -0.0350   1.0000   0.0584
  -9.500  -0.2770   0.09196   0.08668  -0.0364   1.0000   0.0590
  -9.250  -0.2847   0.08772   0.08251  -0.0376   1.0000   0.0593
  -9.000  -0.2968   0.08319   0.07806  -0.0389   1.0000   0.0596
  -8.750  -0.3203   0.07785   0.07284  -0.0401   1.0000   0.0600
  -8.500  -0.3465   0.07410   0.06925  -0.0393   1.0000   0.0603
  -8.250  -0.3260   0.07138   0.06655  -0.0433   0.9857   0.0613
  -8.000  -0.3691   0.03523   0.02900  -0.0926   0.9405   0.0674
  -7.750  -0.3374   0.03307   0.02661  -0.0957   0.9272   0.0699
  -7.500  -0.3073   0.02964   0.02256  -0.0995   0.9139   0.0739
  -7.250  -0.2725   0.02871   0.02158  -0.1012   0.9019   0.0771
  -7.000  -0.2421   0.02690   0.01933  -0.1029   0.8873   0.0821
  -6.750  -0.2095   0.02616   0.01856  -0.1039   0.8736   0.0858
  -6.500  -0.1774   0.02482   0.01680  -0.1051   0.8605   0.0908
  -6.250  -0.1475   0.02425   0.01625  -0.1054   0.8456   0.0943
  -6.000  -0.1182   0.02347   0.01517  -0.1056   0.8307   0.0990
  -5.750  -0.0891   0.02285   0.01447  -0.1057   0.8166   0.1027
  -5.500  -0.0601   0.02241   0.01391  -0.1056   0.8025   0.1070
  -5.250  -0.0331   0.02194   0.01324  -0.1053   0.7872   0.1125
  -5.000  -0.0057   0.02167   0.01297  -0.1049   0.7729   0.1175
  -4.750   0.0224   0.02125   0.01227  -0.1046   0.7592   0.1224
  -4.500   0.0487   0.02073   0.01169  -0.1039   0.7441   0.1251
  -4.250   0.0753   0.02029   0.01120  -0.1033   0.7296   0.1273
  -4.000   0.1024   0.01989   0.01068  -0.1027   0.7160   0.1293
  -3.750   0.1289   0.01953   0.01021  -0.1020   0.7011   0.1319
  -3.500   0.1554   0.01920   0.00976  -0.1013   0.6861   0.1347
  -3.250   0.1821   0.01890   0.00934  -0.1006   0.6720   0.1371
  -3.000   0.2084   0.01860   0.00899  -0.0998   0.6580   0.1395
  -2.750   0.2345   0.01835   0.00872  -0.0991   0.6427   0.1424
  -2.500   0.2609   0.01814   0.00844  -0.0984   0.6284   0.1461
  -2.250   0.2875   0.01796   0.00814  -0.0977   0.6148   0.1507
  -2.000   0.3138   0.01777   0.00794  -0.0970   0.6013   0.1566
  -1.750   0.3403   0.01763   0.00774  -0.0963   0.5878   0.1650
  -1.500   0.3667   0.01748   0.00759  -0.0956   0.5753   0.1763
  -1.250   0.3931   0.01735   0.00745  -0.0950   0.5632   0.1945
  -1.000   0.4198   0.01728   0.00741  -0.0944   0.5507   0.2214
  -0.750   0.4465   0.01728   0.00739  -0.0938   0.5396   0.2533
  -0.500   0.4731   0.01734   0.00747  -0.0932   0.5278   0.2825
  -0.250   0.4997   0.01745   0.00754  -0.0926   0.5173   0.3086
   0.000   0.5261   0.01758   0.00762  -0.0919   0.5069   0.3307
   0.250   0.5524   0.01772   0.00773  -0.0912   0.4973   0.3501
   0.500   0.5785   0.01788   0.00786  -0.0905   0.4874   0.3700
   0.750   0.6046   0.01806   0.00801  -0.0898   0.4785   0.3925
   1.000   0.6306   0.01823   0.00818  -0.0891   0.4689   0.4138
   1.250   0.6570   0.01842   0.00831  -0.0885   0.4605   0.4329
   1.500   0.6832   0.01858   0.00850  -0.0878   0.4509   0.4522
   1.750   0.7097   0.01876   0.00859  -0.0872   0.4429   0.4710
   2.000   0.7360   0.01889   0.00879  -0.0867   0.4330   0.4888
   2.250   0.7624   0.01903   0.00888  -0.0861   0.4249   0.5055
   2.500   0.7887   0.01917   0.00906  -0.0856   0.4156   0.5218
   2.750   0.8149   0.01931   0.00918  -0.0850   0.4072   0.5388
   3.000   0.8407   0.01945   0.00937  -0.0844   0.3984   0.5578
   3.250   0.8662   0.01957   0.00952  -0.0838   0.3896   0.5800
   3.500   0.8914   0.01969   0.00971  -0.0831   0.3813   0.6093
   3.750   0.9155   0.01967   0.00990  -0.0822   0.3726   0.6611
   4.000   0.9512   0.01951   0.01008  -0.0836   0.3637   1.0000
   4.250   0.9759   0.01985   0.01034  -0.0829   0.3548   1.0000
   4.500   1.0002   0.02022   0.01058  -0.0821   0.3474   1.0000
   4.750   1.0242   0.02060   0.01093  -0.0813   0.3388   1.0000
   5.000   1.0479   0.02099   0.01118  -0.0805   0.3320   1.0000
   5.250   1.0712   0.02140   0.01160  -0.0796   0.3238   1.0000
   5.500   1.0941   0.02181   0.01193  -0.0787   0.3167   1.0000
   5.750   1.1169   0.02227   0.01235  -0.0778   0.3097   1.0000
   6.000   1.1392   0.02272   0.01278  -0.0768   0.3026   1.0000
   6.250   1.1613   0.02319   0.01312  -0.0758   0.2968   1.0000
   6.500   1.1829   0.02370   0.01370  -0.0748   0.2898   1.0000
   6.750   1.2041   0.02420   0.01416  -0.0737   0.2837   1.0000
   7.000   1.2251   0.02474   0.01463  -0.0727   0.2783   1.0000
   7.250   1.2453   0.02530   0.01526  -0.0715   0.2720   1.0000
   7.500   1.2652   0.02586   0.01579  -0.0703   0.2665   1.0000
   7.750   1.2853   0.02645   0.01629  -0.0692   0.2619   1.0000
   8.000   1.3037   0.02709   0.01705  -0.0678   0.2562   1.0000
   8.250   1.3219   0.02772   0.01769  -0.0665   0.2511   1.0000
   8.500   1.3403   0.02835   0.01825  -0.0652   0.2468   1.0000
   8.750   1.3570   0.02908   0.01905  -0.0637   0.2421   1.0000
   9.000   1.3724   0.02981   0.01986  -0.0621   0.2372   1.0000
   9.250   1.3877   0.03052   0.02058  -0.0605   0.2329   1.0000
   9.500   1.4039   0.03123   0.02121  -0.0590   0.2291   1.0000
   9.750   1.4138   0.03213   0.02225  -0.0568   0.2248   1.0000
  10.000   1.4239   0.03301   0.02322  -0.0547   0.2205   1.0000
  10.250   1.4346   0.03388   0.02411  -0.0528   0.2166   1.0000
  10.500   1.4483   0.03472   0.02488  -0.0512   0.2131   1.0000
  10.750   1.4543   0.03593   0.02625  -0.0492   0.2093   1.0000
  11.000   1.4602   0.03718   0.02762  -0.0473   0.2052   1.0000
  11.250   1.4674   0.03839   0.02889  -0.0457   0.2015   1.0000
  11.500   1.4772   0.03950   0.02998  -0.0443   0.1982   1.0000
  11.750   1.4818   0.04106   0.03164  -0.0429   0.1948   1.0000
  12.000   1.4820   0.04297   0.03373  -0.0415   0.1910   1.0000
  12.250   1.4844   0.04479   0.03564  -0.0404   0.1875   1.0000
  12.500   1.4895   0.04644   0.03731  -0.0394   0.1842   1.0000
  12.750   1.4960   0.04809   0.03896  -0.0386   0.1812   1.0000
  13.000   1.4884   0.05112   0.04223  -0.0381   0.1778   1.0000
  13.250   1.4835   0.05401   0.04527  -0.0377   0.1744   1.0000
  13.500   1.4830   0.05653   0.04786  -0.0375   0.1713   1.0000
  13.750   1.4883   0.05846   0.04979  -0.0372   0.1686   1.0000
  14.000   1.4798   0.06212   0.05360  -0.0375   0.1657   1.0000
  14.250   1.4619   0.06714   0.05886  -0.0385   0.1626   1.0000
  14.500   1.4493   0.07170   0.06357  -0.0396   0.1595   1.0000
  14.750   1.4467   0.07499   0.06692  -0.0403   0.1568   1.0000
  15.000   1.4571   0.07648   0.06836  -0.0401   0.1544   1.0000
  15.250   1.4121   0.08647   0.07870  -0.0442   0.1513   1.0000
  15.500   1.3310   0.10355   0.09618  -0.0526   0.1468   1.0000
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