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E201 (11.88%) (e201-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E201 (11.88%) (e201-il)
Reynolds number: 50,000
Max Cl/Cd: 33.93 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e201-il-50000-n5.txt
Download as CSV file: xf-e201-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E201  (11.88%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3913   0.09798   0.09090  -0.0445   1.0000   0.0521
  -9.500  -0.3935   0.09396   0.08697  -0.0458   1.0000   0.0517
  -9.250  -0.3972   0.08983   0.08293  -0.0472   1.0000   0.0513
  -9.000  -0.4033   0.08552   0.07873  -0.0487   1.0000   0.0508
  -8.750  -0.4125   0.08098   0.07430  -0.0504   1.0000   0.0502
  -8.500  -0.4263   0.07611   0.06955  -0.0524   1.0000   0.0495
  -8.250  -0.4474   0.07120   0.06476  -0.0544   1.0000   0.0488
  -8.000  -0.4666   0.06677   0.06036  -0.0552   1.0000   0.0481
  -7.750  -0.4839   0.06273   0.05629  -0.0550   1.0000   0.0476
  -7.500  -0.4984   0.05897   0.05243  -0.0541   1.0000   0.0473
  -7.250  -0.5095   0.05542   0.04871  -0.0528   1.0000   0.0470
  -7.000  -0.5165   0.05208   0.04513  -0.0513   1.0000   0.0468
  -6.750  -0.5192   0.04891   0.04166  -0.0498   1.0000   0.0467
  -6.500  -0.5061   0.04512   0.03741  -0.0508   0.9957   0.0470
  -6.250  -0.4761   0.04109   0.03276  -0.0542   0.9863   0.0478
  -6.000  -0.4449   0.03780   0.02887  -0.0566   0.9771   0.0490
  -5.750  -0.4116   0.03508   0.02561  -0.0588   0.9685   0.0510
  -5.500  -0.3779   0.03291   0.02292  -0.0605   0.9596   0.0547
  -5.250  -0.3469   0.03134   0.02129  -0.0619   0.9500   0.0595
  -5.000  -0.3109   0.02969   0.01930  -0.0635   0.9427   0.0648
  -4.750  -0.2812   0.02826   0.01777  -0.0642   0.9327   0.0714
  -4.500  -0.2497   0.02700   0.01644  -0.0653   0.9237   0.0869
  -4.250  -0.2152   0.02565   0.01515  -0.0672   0.9159   0.1224
  -4.000  -0.1856   0.02440   0.01426  -0.0686   0.9063   0.1907
  -3.750  -0.1497   0.02321   0.01344  -0.0709   0.8999   0.2839
  -3.500  -0.1240   0.02263   0.01321  -0.0708   0.8896   0.3753
  -3.250  -0.0950   0.02232   0.01302  -0.0708   0.8810   0.4615
  -3.000  -0.0656   0.02208   0.01284  -0.0707   0.8728   0.5282
  -2.750  -0.0402   0.02195   0.01268  -0.0698   0.8635   0.5831
  -2.500  -0.0100   0.02174   0.01247  -0.0695   0.8567   0.6351
  -2.250   0.0127   0.02165   0.01239  -0.0679   0.8469   0.6798
  -2.000   0.0432   0.02145   0.01215  -0.0675   0.8409   0.7276
  -1.750   0.0648   0.02142   0.01212  -0.0656   0.8311   0.7722
  -1.500   0.0979   0.02126   0.01191  -0.0656   0.8249   0.8234
  -1.250   0.1357   0.02124   0.01181  -0.0670   0.8169   0.8773
  -1.000   0.1969   0.02107   0.01145  -0.0731   0.8124   0.9331
  -0.750   0.2569   0.02101   0.01115  -0.0799   0.8052   0.9865
  -0.500   0.2898   0.02102   0.01093  -0.0817   0.7980   1.0000
  -0.250   0.3065   0.02129   0.01101  -0.0805   0.7881   1.0000
   0.000   0.3351   0.02138   0.01089  -0.0808   0.7817   1.0000
   0.250   0.3527   0.02176   0.01114  -0.0796   0.7720   1.0000
   0.500   0.3805   0.02193   0.01115  -0.0798   0.7654   1.0000
   0.750   0.4010   0.02232   0.01144  -0.0789   0.7565   1.0000
   1.000   0.4282   0.02255   0.01155  -0.0789   0.7501   1.0000
   1.250   0.4496   0.02297   0.01189  -0.0782   0.7416   1.0000
   1.500   0.4770   0.02322   0.01207  -0.0782   0.7354   1.0000
   1.750   0.4978   0.02370   0.01251  -0.0774   0.7269   1.0000
   2.000   0.5261   0.02394   0.01269  -0.0774   0.7210   1.0000
   2.250   0.5456   0.02451   0.01325  -0.0765   0.7124   1.0000
   2.500   0.5759   0.02469   0.01342  -0.0767   0.7071   1.0000
   2.750   0.5930   0.02539   0.01413  -0.0755   0.6979   1.0000
   3.000   0.6237   0.02556   0.01430  -0.0758   0.6927   1.0000
   3.250   0.6396   0.02633   0.01512  -0.0744   0.6832   1.0000
   3.500   0.6704   0.02651   0.01534  -0.0746   0.6780   1.0000
   3.750   0.6859   0.02732   0.01623  -0.0732   0.6683   1.0000
   4.000   0.7173   0.02746   0.01642  -0.0735   0.6631   1.0000
   4.250   0.7319   0.02833   0.01737  -0.0720   0.6529   1.0000
   4.500   0.7587   0.02865   0.01780  -0.0716   0.6460   1.0000
   5.000   0.7991   0.02984   0.01920  -0.0696   0.6275   1.0000
   5.250   0.8284   0.02994   0.01942  -0.0694   0.6200   1.0000
   5.500   0.8446   0.03068   0.02032  -0.0678   0.6089   1.0000
   5.750   0.8679   0.03102   0.02080  -0.0669   0.5992   1.0000
   6.000   0.8976   0.03096   0.02088  -0.0665   0.5901   1.0000
   6.250   0.9149   0.03149   0.02158  -0.0649   0.5776   1.0000
   6.500   0.9349   0.03182   0.02211  -0.0634   0.5651   1.0000
   6.750   0.9567   0.03196   0.02243  -0.0620   0.5520   1.0000
   7.000   0.9789   0.03199   0.02265  -0.0606   0.5381   1.0000
   7.250   1.0004   0.03197   0.02281  -0.0589   0.5229   1.0000
   7.500   1.0216   0.03185   0.02292  -0.0571   0.5062   1.0000
   7.750   1.0447   0.03150   0.02273  -0.0554   0.4880   1.0000
   8.000   1.0557   0.03184   0.02326  -0.0526   0.4668   1.0000
   8.250   1.0736   0.03164   0.02318  -0.0502   0.4435   1.0000
   8.500   1.0816   0.03210   0.02379  -0.0472   0.4168   1.0000
   8.750   1.0898   0.03245   0.02423  -0.0440   0.3868   1.0000
   9.000   1.0941   0.03317   0.02495  -0.0407   0.3529   1.0000
   9.250   1.0978   0.03409   0.02572  -0.0375   0.3150   1.0000
   9.500   1.0972   0.03560   0.02704  -0.0346   0.2776   1.0000
   9.750   1.0938   0.03756   0.02876  -0.0320   0.2440   1.0000
  10.000   1.0893   0.03991   0.03091  -0.0298   0.2147   1.0000
  10.250   1.0847   0.04250   0.03338  -0.0282   0.1886   1.0000
  10.500   1.0806   0.04525   0.03604  -0.0268   0.1655   1.0000
  10.750   1.0756   0.04821   0.03885  -0.0256   0.1460   1.0000
  11.000   1.0716   0.05127   0.04185  -0.0248   0.1258   1.0000
  11.250   1.0666   0.05454   0.04502  -0.0243   0.1082   1.0000
  11.500   1.0616   0.05792   0.04830  -0.0241   0.0932   1.0000
  11.750   1.0583   0.06127   0.05165  -0.0239   0.0805   1.0000
  12.000   1.0565   0.06459   0.05500  -0.0237   0.0695   1.0000
  12.250   1.0570   0.06774   0.05822  -0.0234   0.0614   1.0000
  12.500   1.0562   0.07100   0.06143  -0.0232   0.0560   1.0000
  12.750   1.0615   0.07387   0.06453  -0.0227   0.0503   1.0000
  13.000   1.0629   0.07701   0.06770  -0.0228   0.0466   1.0000
  13.250   1.0679   0.08003   0.07090  -0.0224   0.0433   1.0000
  13.500   1.0736   0.08318   0.07434  -0.0221   0.0408   1.0000
  13.750   1.0775   0.08658   0.07796  -0.0221   0.0391   1.0000
  14.000   1.0795   0.09023   0.08180  -0.0225   0.0378   1.0000
  14.250   1.0803   0.09410   0.08583  -0.0231   0.0368   1.0000
  14.500   1.0808   0.09813   0.08998  -0.0238   0.0359   1.0000
  14.750   1.0729   0.10362   0.09574  -0.0257   0.0356   1.0000
  15.000   1.0604   0.11002   0.10242  -0.0286   0.0354   1.0000
  15.250   1.0458   0.11717   0.10977  -0.0323   0.0353   1.0000
  15.500   1.0299   0.12501   0.11783  -0.0367   0.0354   1.0000
  15.750   1.0138   0.13343   0.12643  -0.0416   0.0355   1.0000
  16.000   0.9976   0.14254   0.13567  -0.0471   0.0357   1.0000
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