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E474 (14.09%) (e474-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E474 (14.09%) (e474-il)
Reynolds number: 50,000
Max Cl/Cd: 18.21 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e474-il-50000.txt
Download as CSV file: xf-e474-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E474  (14.09%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4244   0.10580   0.09689   0.0149   1.0000   0.4536
  -9.000  -0.4319   0.10403   0.09516   0.0156   1.0000   0.4656
  -8.750  -0.4289   0.10217   0.09330   0.0165   1.0000   0.4805
  -8.500  -0.3994   0.09812   0.08920   0.0162   1.0000   0.4935
  -8.250  -0.3878   0.09524   0.08632   0.0165   1.0000   0.5056
  -8.000  -0.3873   0.09308   0.08419   0.0173   1.0000   0.5184
  -7.750  -0.3905   0.09154   0.08268   0.0188   1.0000   0.5331
  -7.500  -0.5743   0.07149   0.06284   0.0018   1.0000   0.3625
  -7.250  -0.5909   0.06663   0.05800   0.0020   1.0000   0.3600
  -7.000  -0.6140   0.06138   0.05276   0.0023   1.0000   0.3583
  -6.750  -0.6414   0.05603   0.04734   0.0033   1.0000   0.3577
  -6.500  -0.6637   0.05119   0.04236   0.0050   1.0000   0.3585
  -6.250  -0.6822   0.04681   0.03769   0.0071   1.0000   0.3613
  -6.000  -0.6598   0.04571   0.03667   0.0087   1.0000   0.3676
  -5.750  -0.6554   0.04331   0.03413   0.0105   1.0000   0.3732
  -5.500  -0.6584   0.04026   0.03075   0.0126   1.0000   0.3780
  -5.250  -0.6402   0.03888   0.02942   0.0141   1.0000   0.3837
  -5.000  -0.6281   0.03724   0.02767   0.0158   1.0000   0.3909
  -4.750  -0.6182   0.03535   0.02556   0.0175   1.0000   0.3976
  -4.500  -0.5995   0.03422   0.02446   0.0190   1.0000   0.4042
  -4.250  -0.5878   0.03258   0.02256   0.0206   1.0000   0.4118
  -4.000  -0.5682   0.03159   0.02166   0.0220   1.0000   0.4193
  -3.750  -0.5528   0.03036   0.02025   0.0234   1.0000   0.4282
  -3.500  -0.5336   0.02938   0.01931   0.0248   1.0000   0.4358
  -3.250  -0.5164   0.02836   0.01818   0.0260   1.0000   0.4453
  -3.000  -0.4969   0.02755   0.01745   0.0274   1.0000   0.4544
  -2.750  -0.4789   0.02668   0.01649   0.0286   1.0000   0.4652
  -2.500  -0.4591   0.02599   0.01589   0.0298   1.0000   0.4754
  -2.250  -0.4401   0.02532   0.01526   0.0310   1.0000   0.4868
  -2.000  -0.4216   0.02472   0.01466   0.0321   1.0000   0.4999
  -1.750  -0.4031   0.02422   0.01423   0.0333   1.0000   0.5138
  -1.500  -0.3846   0.02380   0.01396   0.0344   1.0000   0.5282
  -1.250  -0.3672   0.02348   0.01377   0.0355   1.0000   0.5450
  -1.000  -0.3514   0.02327   0.01369   0.0365   1.0000   0.5643
  -0.750  -0.3392   0.02321   0.01382   0.0376   1.0000   0.5850
  -0.500  -0.2531   0.02341   0.01452   0.0261   0.9624   0.6385
  -0.250  -0.1596   0.02280   0.01465   0.0160   0.9124   0.7234
   0.000  -0.0001   0.02256   0.01509   0.0000   0.8469   0.8467
   0.250   0.1596   0.02280   0.01465  -0.0160   0.7233   0.9124
   0.500   0.2533   0.02342   0.01452  -0.0261   0.6381   0.9626
   0.750   0.3391   0.02321   0.01382  -0.0376   0.5849   1.0000
   1.000   0.3513   0.02327   0.01369  -0.0365   0.5640   1.0000
   1.250   0.3672   0.02348   0.01377  -0.0355   0.5451   1.0000
   1.500   0.3845   0.02380   0.01396  -0.0344   0.5283   1.0000
   1.750   0.4030   0.02422   0.01423  -0.0333   0.5139   1.0000
   2.000   0.4215   0.02471   0.01465  -0.0321   0.5000   1.0000
   2.250   0.4400   0.02531   0.01525  -0.0310   0.4867   1.0000
   2.500   0.4590   0.02599   0.01589  -0.0298   0.4754   1.0000
   2.750   0.4788   0.02668   0.01648  -0.0286   0.4652   1.0000
   3.000   0.4968   0.02755   0.01746  -0.0274   0.4545   1.0000
   3.250   0.5164   0.02836   0.01818  -0.0260   0.4454   1.0000
   3.500   0.5336   0.02937   0.01931  -0.0248   0.4358   1.0000
   3.750   0.5527   0.03036   0.02025  -0.0234   0.4281   1.0000
   4.000   0.5681   0.03158   0.02165  -0.0220   0.4193   1.0000
   4.250   0.5877   0.03258   0.02256  -0.0206   0.4118   1.0000
   4.500   0.5995   0.03421   0.02446  -0.0190   0.4042   1.0000
   4.750   0.6182   0.03534   0.02555  -0.0175   0.3976   1.0000
   5.000   0.6281   0.03724   0.02766  -0.0158   0.3908   1.0000
   5.250   0.6402   0.03888   0.02942  -0.0141   0.3838   1.0000
   5.500   0.6585   0.04024   0.03073  -0.0126   0.3781   1.0000
   5.750   0.6554   0.04330   0.03413  -0.0105   0.3732   1.0000
   6.000   0.6599   0.04570   0.03666  -0.0087   0.3676   1.0000
   6.250   0.6824   0.04679   0.03767  -0.0071   0.3614   1.0000
   6.500   0.6638   0.05118   0.04234  -0.0050   0.3585   1.0000
   6.750   0.6415   0.05602   0.04733  -0.0034   0.3577   1.0000
   7.000   0.6140   0.06138   0.05275  -0.0023   0.3583   1.0000
   7.250   0.5912   0.06660   0.05798  -0.0020   0.3599   1.0000
   7.500   0.5746   0.07148   0.06283  -0.0019   0.3625   1.0000
   7.750   0.3910   0.09150   0.08264  -0.0188   0.5332   1.0000
   8.000   0.3873   0.09303   0.08412  -0.0174   0.5185   1.0000
   8.250   0.3887   0.09524   0.08631  -0.0166   0.5055   1.0000
   8.500   0.4003   0.09812   0.08919  -0.0163   0.4936   1.0000
   8.750   0.4324   0.10236   0.09349  -0.0167   0.4807   1.0000
   9.000   0.4325   0.10400   0.09513  -0.0157   0.4657   1.0000
   9.250   0.4251   0.10577   0.09686  -0.0150   0.4538   1.0000
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