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EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E853 AIRFOIL (e853-il)
Reynolds number: 50,000
Max Cl/Cd: 35.91 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e853-il-50000-n5.txt
Download as CSV file: xf-e853-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E853 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3981   0.10171   0.09477  -0.0478   1.0000   0.0370
  -9.500  -0.4020   0.09764   0.09079  -0.0489   1.0000   0.0371
  -9.250  -0.4075   0.09336   0.08662  -0.0502   1.0000   0.0364
  -8.750  -0.4467   0.07908   0.07252  -0.0584   1.0000   0.0321
  -8.500  -0.4600   0.07576   0.06929  -0.0584   1.0000   0.0318
  -8.250  -0.4778   0.07267   0.06629  -0.0580   1.0000   0.0316
  -8.000  -0.4941   0.06922   0.06289  -0.0583   1.0000   0.0314
  -7.750  -0.5075   0.06611   0.05975  -0.0577   1.0000   0.0311
  -7.500  -0.5212   0.06268   0.05622  -0.0572   1.0000   0.0312
  -7.250  -0.5295   0.05942   0.05282  -0.0565   1.0000   0.0311
  -7.000  -0.5343   0.05599   0.04914  -0.0561   1.0000   0.0313
  -6.750  -0.5341   0.05251   0.04526  -0.0559   1.0000   0.0318
  -6.500  -0.5296   0.04893   0.04137  -0.0558   1.0000   0.0327
  -6.250  -0.5129   0.04588   0.03814  -0.0573   0.9973   0.0349
  -6.000  -0.4826   0.04228   0.03405  -0.0606   0.9914   0.0371
  -5.750  -0.4507   0.03872   0.02989  -0.0631   0.9856   0.0386
  -5.500  -0.4176   0.03571   0.02630  -0.0648   0.9805   0.0411
  -5.250  -0.3869   0.03350   0.02376  -0.0661   0.9744   0.0472
  -5.000  -0.3535   0.03173   0.02160  -0.0672   0.9696   0.0549
  -4.750  -0.3259   0.03017   0.01995  -0.0676   0.9628   0.0653
  -4.500  -0.2931   0.02863   0.01822  -0.0689   0.9576   0.0821
  -4.000  -0.2305   0.02516   0.01518  -0.0731   0.9456   0.1736
  -3.750  -0.2034   0.02361   0.01501  -0.0744   0.9392   0.4113
  -3.500  -0.1736   0.02400   0.01533  -0.0742   0.9325   0.5156
  -3.250  -0.1490   0.02437   0.01548  -0.0731   0.9248   0.5663
  -3.000  -0.1216   0.02473   0.01571  -0.0722   0.9186   0.6090
  -2.750  -0.1003   0.02499   0.01586  -0.0702   0.9109   0.6397
  -2.500  -0.0709   0.02507   0.01574  -0.0702   0.9053   0.6650
  -2.250  -0.0457   0.02509   0.01556  -0.0697   0.8983   0.6809
  -2.000  -0.0147   0.02503   0.01525  -0.0705   0.8925   0.6950
  -1.750   0.0142   0.02501   0.01503  -0.0711   0.8865   0.7081
  -1.500   0.0431   0.02499   0.01484  -0.0717   0.8803   0.7208
  -1.250   0.0779   0.02492   0.01460  -0.0732   0.8761   0.7333
  -1.000   0.0993   0.02500   0.01457  -0.0725   0.8682   0.7451
  -0.750   0.1321   0.02497   0.01442  -0.0737   0.8638   0.7581
  -0.500   0.1551   0.02507   0.01446  -0.0732   0.8567   0.7712
  -0.250   0.1848   0.02508   0.01440  -0.0739   0.8515   0.7854
   0.000   0.2115   0.02514   0.01441  -0.0740   0.8460   0.8008
   0.250   0.2359   0.02524   0.01450  -0.0737   0.8395   0.8178
   0.500   0.2676   0.02519   0.01445  -0.0745   0.8356   0.8362
   0.750   0.2847   0.02541   0.01471  -0.0730   0.8277   0.8592
   1.000   0.3167   0.02538   0.01472  -0.0739   0.8232   0.8874
   1.250   0.3489   0.02554   0.01494  -0.0755   0.8171   0.9324
   1.500   0.3866   0.02572   0.01510  -0.0785   0.8112   1.0000
   1.750   0.4275   0.02591   0.01525  -0.0817   0.8077   1.0000
   2.000   0.4476   0.02654   0.01583  -0.0817   0.7992   1.0000
   2.250   0.4849   0.02680   0.01606  -0.0840   0.7950   1.0000
   2.500   0.5057   0.02744   0.01669  -0.0838   0.7869   1.0000
   2.750   0.5402   0.02775   0.01706  -0.0855   0.7820   1.0000
   3.000   0.5620   0.02838   0.01771  -0.0853   0.7741   1.0000
   3.250   0.5948   0.02871   0.01811  -0.0865   0.7686   1.0000
   3.500   0.6165   0.02934   0.01880  -0.0861   0.7603   1.0000
   3.750   0.6500   0.02961   0.01923  -0.0873   0.7545   1.0000
   4.000   0.6701   0.03027   0.01998  -0.0866   0.7452   1.0000
   4.250   0.7076   0.03035   0.02023  -0.0880   0.7396   1.0000
   4.500   0.7265   0.03101   0.02102  -0.0870   0.7291   1.0000
   4.750   0.7528   0.03139   0.02162  -0.0869   0.7199   1.0000
   5.000   0.7897   0.03129   0.02174  -0.0878   0.7121   1.0000
   5.250   0.8130   0.03161   0.02227  -0.0869   0.7001   1.0000
   5.500   0.8405   0.03162   0.02250  -0.0863   0.6873   1.0000
   5.750   0.8732   0.03116   0.02231  -0.0858   0.6728   1.0000
   6.000   0.9114   0.03008   0.02159  -0.0854   0.6550   1.0000
   6.250   0.9354   0.02947   0.02123  -0.0832   0.6314   1.0000
   6.500   0.9582   0.02880   0.02080  -0.0807   0.6044   1.0000
   6.750   0.9781   0.02823   0.02044  -0.0778   0.5727   1.0000
   7.000   0.9872   0.02823   0.02064  -0.0740   0.5335   1.0000
   7.250   0.9973   0.02817   0.02064  -0.0700   0.4756   1.0000
   7.500   1.0119   0.02818   0.01994  -0.0660   0.3544   1.0000
   7.750   1.0069   0.03015   0.02118  -0.0616   0.2656   1.0000
   8.000   1.0005   0.03256   0.02308  -0.0580   0.2056   1.0000
   8.250   0.9971   0.03501   0.02528  -0.0551   0.1634   1.0000
   8.500   0.9971   0.03743   0.02745  -0.0528   0.1342   1.0000
   8.750   0.9999   0.03975   0.02963  -0.0508   0.1101   1.0000
   9.000   1.0062   0.04199   0.03182  -0.0489   0.0937   1.0000
   9.250   1.0164   0.04412   0.03399  -0.0473   0.0787   1.0000
   9.500   1.0292   0.04617   0.03609  -0.0459   0.0656   1.0000
   9.750   1.0526   0.04816   0.03815  -0.0447   0.0552   1.0000
  10.000   1.0690   0.05025   0.04033  -0.0438   0.0467   1.0000
  10.250   1.1087   0.05317   0.04369  -0.0433   0.0399   1.0000
  10.500   1.1190   0.05571   0.04636  -0.0423   0.0358   1.0000
  10.750   1.1313   0.05918   0.05013  -0.0413   0.0328   1.0000
  11.000   1.1386   0.06314   0.05460  -0.0399   0.0314   1.0000
  11.250   1.1375   0.06722   0.05910  -0.0385   0.0306   1.0000
  11.500   1.1304   0.07146   0.06372  -0.0372   0.0300   1.0000
  11.750   1.1192   0.07590   0.06850  -0.0365   0.0297   1.0000
  12.000   1.1048   0.08067   0.07356  -0.0363   0.0295   1.0000
  12.250   1.0878   0.08586   0.07904  -0.0368   0.0293   1.0000
  12.500   1.0690   0.09159   0.08502  -0.0383   0.0295   1.0000
  12.750   1.0486   0.09793   0.09158  -0.0406   0.0297   1.0000
  13.000   1.0276   0.10495   0.09880  -0.0440   0.0301   1.0000
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