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E224 (10.17%) (e224-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E224 (10.17%) (e224-il)
Reynolds number: 50,000
Max Cl/Cd: 35.81 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e224-il-50000-n5.txt
Download as CSV file: xf-e224-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E224  (10.17%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4941   0.09868   0.09149  -0.0292   1.0000   0.0424
  -9.750  -0.4980   0.09367   0.08657  -0.0316   1.0000   0.0423
  -9.500  -0.5040   0.08819   0.08118  -0.0344   1.0000   0.0420
  -9.250  -0.5124   0.08207   0.07515  -0.0380   1.0000   0.0413
  -9.000  -0.5275   0.07459   0.06774  -0.0432   1.0000   0.0400
  -8.500  -0.5902   0.06043   0.05329  -0.0503   1.0000   0.0361
  -8.250  -0.5956   0.05681   0.04954  -0.0499   1.0000   0.0366
  -8.000  -0.5964   0.05363   0.04622  -0.0491   1.0000   0.0375
  -7.750  -0.5938   0.05074   0.04317  -0.0481   1.0000   0.0389
  -7.500  -0.5903   0.04751   0.03967  -0.0471   1.0000   0.0401
  -7.250  -0.5844   0.04412   0.03585  -0.0459   1.0000   0.0412
  -7.000  -0.5751   0.04081   0.03211  -0.0445   1.0000   0.0422
  -6.750  -0.5623   0.03779   0.02863  -0.0431   1.0000   0.0435
  -6.500  -0.5467   0.03503   0.02538  -0.0415   1.0000   0.0456
  -6.250  -0.5305   0.03291   0.02305  -0.0402   1.0000   0.0495
  -6.000  -0.5131   0.03125   0.02121  -0.0388   1.0000   0.0554
  -5.750  -0.4941   0.02932   0.01900  -0.0372   1.0000   0.0604
  -5.500  -0.4761   0.02793   0.01750  -0.0358   1.0000   0.0703
  -5.250  -0.4580   0.02644   0.01594  -0.0343   1.0000   0.0817
  -5.000  -0.4394   0.02509   0.01455  -0.0329   1.0000   0.0998
  -4.750  -0.4207   0.02379   0.01333  -0.0317   1.0000   0.1270
  -4.500  -0.4017   0.02260   0.01235  -0.0308   1.0000   0.1696
  -4.250  -0.3819   0.02158   0.01159  -0.0301   1.0000   0.2272
  -4.000  -0.3628   0.02081   0.01103  -0.0290   1.0000   0.2898
  -3.750  -0.3436   0.02023   0.01062  -0.0279   1.0000   0.3536
  -3.500  -0.3246   0.01977   0.01029  -0.0265   1.0000   0.4144
  -3.250  -0.3057   0.01942   0.01007  -0.0249   1.0000   0.4732
  -3.000  -0.2872   0.01916   0.00993  -0.0231   1.0000   0.5298
  -2.750  -0.2692   0.01897   0.00983  -0.0211   1.0000   0.5842
  -2.500  -0.2522   0.01883   0.00979  -0.0189   1.0000   0.6362
  -2.250  -0.2361   0.01874   0.00974  -0.0164   1.0000   0.6876
  -2.000  -0.2155   0.01872   0.00977  -0.0147   0.9969   0.7423
  -1.750  -0.1832   0.01880   0.00987  -0.0150   0.9872   0.8030
  -1.500  -0.1453   0.01889   0.00991  -0.0163   0.9783   0.8666
  -1.250  -0.0894   0.01900   0.00983  -0.0216   0.9717   0.9329
  -1.000  -0.0232   0.01902   0.00961  -0.0298   0.9651   1.0000
  -0.750   0.0151   0.01914   0.00947  -0.0330   0.9535   1.0000
  -0.500   0.0550   0.01927   0.00941  -0.0362   0.9423   1.0000
  -0.250   0.0913   0.01939   0.00936  -0.0386   0.9297   1.0000
   0.000   0.1277   0.01950   0.00932  -0.0408   0.9172   1.0000
   0.250   0.1644   0.01961   0.00932  -0.0429   0.9048   1.0000
   0.500   0.2019   0.01970   0.00933  -0.0450   0.8926   1.0000
   0.750   0.2397   0.01977   0.00934  -0.0471   0.8806   1.0000
   1.000   0.2760   0.01982   0.00935  -0.0487   0.8680   1.0000
   1.250   0.3111   0.01986   0.00937  -0.0500   0.8550   1.0000
   1.500   0.3445   0.01989   0.00940  -0.0509   0.8411   1.0000
   1.750   0.3760   0.01993   0.00944  -0.0514   0.8263   1.0000
   2.000   0.4062   0.01998   0.00951  -0.0516   0.8108   1.0000
   2.250   0.4361   0.02003   0.00960  -0.0516   0.7946   1.0000
   2.500   0.4657   0.02008   0.00968  -0.0515   0.7781   1.0000
   2.750   0.4955   0.02010   0.00975  -0.0514   0.7612   1.0000
   3.000   0.5255   0.02012   0.00983  -0.0512   0.7440   1.0000
   3.250   0.5522   0.02021   0.00998  -0.0505   0.7246   1.0000
   3.500   0.5792   0.02030   0.01012  -0.0498   0.7047   1.0000
   3.750   0.6071   0.02036   0.01022  -0.0491   0.6847   1.0000
   4.000   0.6321   0.02052   0.01049  -0.0481   0.6621   1.0000
   4.250   0.6580   0.02066   0.01067  -0.0471   0.6393   1.0000
   4.500   0.6837   0.02082   0.01087  -0.0461   0.6154   1.0000
   4.750   0.7075   0.02106   0.01116  -0.0449   0.5893   1.0000
   5.000   0.7312   0.02132   0.01152  -0.0436   0.5622   1.0000
   5.250   0.7543   0.02162   0.01186  -0.0423   0.5336   1.0000
   5.500   0.7768   0.02197   0.01222  -0.0409   0.5037   1.0000
   5.750   0.7986   0.02238   0.01262  -0.0395   0.4725   1.0000
   6.000   0.8189   0.02287   0.01314  -0.0379   0.4390   1.0000
   6.250   0.8386   0.02343   0.01374  -0.0363   0.4047   1.0000
   6.500   0.8572   0.02408   0.01436  -0.0347   0.3696   1.0000
   6.750   0.8747   0.02483   0.01507  -0.0330   0.3334   1.0000
   7.000   0.8912   0.02570   0.01589  -0.0313   0.2970   1.0000
   7.250   0.9065   0.02669   0.01680  -0.0295   0.2618   1.0000
   7.500   0.9211   0.02782   0.01786  -0.0278   0.2275   1.0000
   7.750   0.9348   0.02909   0.01907  -0.0261   0.1958   1.0000
   8.000   0.9480   0.03051   0.02049  -0.0244   0.1679   1.0000
   8.250   0.9599   0.03205   0.02197  -0.0227   0.1424   1.0000
   8.500   0.9706   0.03371   0.02352  -0.0210   0.1222   1.0000
   8.750   0.9824   0.03543   0.02530  -0.0193   0.1041   1.0000
   9.000   0.9934   0.03724   0.02717  -0.0177   0.0899   1.0000
   9.250   1.0052   0.03922   0.02918  -0.0161   0.0800   1.0000
   9.500   1.0158   0.04112   0.03117  -0.0144   0.0714   1.0000
   9.750   1.0282   0.04328   0.03357  -0.0129   0.0643   1.0000
  10.000   1.0414   0.04554   0.03600  -0.0116   0.0597   1.0000
  10.250   1.0563   0.04835   0.03900  -0.0105   0.0561   1.0000
  10.500   1.0629   0.05119   0.04225  -0.0089   0.0527   1.0000
  10.750   1.0649   0.05369   0.04496  -0.0072   0.0495   1.0000
  11.000   1.0685   0.05620   0.04752  -0.0060   0.0470   1.0000
  11.250   1.0667   0.05978   0.05136  -0.0047   0.0456   1.0000
  11.500   1.0579   0.06370   0.05567  -0.0037   0.0450   1.0000
  11.750   1.0449   0.06805   0.06036  -0.0035   0.0445   1.0000
  12.000   1.0289   0.07291   0.06551  -0.0042   0.0443   1.0000
  12.250   1.0101   0.07845   0.07130  -0.0060   0.0442   1.0000
  12.500   0.9897   0.08473   0.07779  -0.0089   0.0444   1.0000
  12.750   0.9680   0.09189   0.08512  -0.0130   0.0447   1.0000
  13.000   0.9452   0.10011   0.09347  -0.0182   0.0451   1.0000
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