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EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E850 AIRFOIL (e850-il)
Reynolds number: 200,000
Max Cl/Cd: 62.2 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e850-il-200000-n5.txt
Download as CSV file: xf-e850-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E850 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.5727   0.06107   0.05759  -0.0381   1.0000   0.0100
  -6.750  -0.5703   0.05573   0.05207  -0.0408   0.9983   0.0095
  -6.500  -0.5559   0.04965   0.04570  -0.0452   0.9949   0.0088
  -6.250  -0.5377   0.04433   0.04004  -0.0481   0.9922   0.0081
  -6.000  -0.5177   0.03951   0.03483  -0.0498   0.9891   0.0075
  -5.750  -0.4945   0.03485   0.02971  -0.0511   0.9865   0.0069
  -5.500  -0.4688   0.03045   0.02479  -0.0519   0.9845   0.0062
  -5.250  -0.4406   0.02664   0.02040  -0.0524   0.9829   0.0057
  -5.000  -0.4113   0.02362   0.01688  -0.0527   0.9818   0.0053
  -4.750  -0.3825   0.02133   0.01407  -0.0527   0.9807   0.0050
  -4.500  -0.3574   0.01965   0.01213  -0.0521   0.9787   0.0048
  -4.250  -0.3310   0.01827   0.01056  -0.0518   0.9768   0.0047
  -4.000  -0.3036   0.01704   0.00916  -0.0518   0.9749   0.0047
  -3.750  -0.2752   0.01594   0.00790  -0.0522   0.9732   0.0047
  -3.500  -0.2453   0.01511   0.00686  -0.0528   0.9717   0.0050
  -3.250  -0.2142   0.01454   0.00605  -0.0536   0.9702   0.0055
  -3.000  -0.1823   0.01416   0.00546  -0.0545   0.9689   0.0069
  -2.750  -0.1556   0.01341   0.00500  -0.0548   0.9666   0.0787
  -2.500  -0.1312   0.01178   0.00466  -0.0557   0.9646   0.4142
  -2.250  -0.1061   0.01148   0.00498  -0.0552   0.9620   0.5814
  -2.000  -0.0768   0.01148   0.00499  -0.0556   0.9597   0.6136
  -1.750  -0.0457   0.01147   0.00494  -0.0564   0.9578   0.6275
  -1.500  -0.0133   0.01146   0.00490  -0.0575   0.9562   0.6383
  -1.250   0.0125   0.01144   0.00488  -0.0572   0.9527   0.6478
  -1.000   0.0404   0.01143   0.00483  -0.0573   0.9494   0.6580
  -0.750   0.0710   0.01141   0.00481  -0.0581   0.9468   0.6684
  -0.500   0.1033   0.01139   0.00481  -0.0592   0.9446   0.6799
  -0.250   0.1372   0.01137   0.00482  -0.0606   0.9429   0.6918
   0.000   0.1604   0.01135   0.00486  -0.0597   0.9374   0.7039
   0.250   0.1916   0.01130   0.00489  -0.0605   0.9340   0.7169
   0.500   0.2258   0.01122   0.00489  -0.0619   0.9314   0.7311
   0.750   0.2545   0.01115   0.00494  -0.0621   0.9269   0.7462
   1.000   0.2841   0.01106   0.00496  -0.0625   0.9218   0.7630
   1.250   0.3204   0.01088   0.00492  -0.0641   0.9185   0.7816
   1.500   0.3486   0.01072   0.00492  -0.0640   0.9114   0.8026
   1.750   0.3866   0.01038   0.00477  -0.0657   0.9059   0.8257
   2.000   0.4205   0.01000   0.00472  -0.0663   0.8948   0.8533
   2.250   0.4578   0.00941   0.00433  -0.0671   0.8734   0.8864
   2.500   0.4982   0.00891   0.00400  -0.0688   0.8391   0.9305
   2.750   0.5536   0.00890   0.00331  -0.0729   0.6294   0.9634
   3.000   0.5571   0.01064   0.00373  -0.0682   0.3655   1.0000
   3.250   0.5691   0.01206   0.00427  -0.0658   0.1764   1.0000
   3.500   0.5877   0.01312   0.00495  -0.0644   0.0738   1.0000
   3.750   0.6083   0.01412   0.00571  -0.0632   0.0283   1.0000
   4.000   0.6299   0.01508   0.00671  -0.0619   0.0134   1.0000
   4.250   0.6515   0.01614   0.00793  -0.0604   0.0108   1.0000
   4.500   0.6731   0.01745   0.00937  -0.0590   0.0096   1.0000
   4.750   0.6967   0.01903   0.01108  -0.0578   0.0089   1.0000
   5.000   0.7225   0.02094   0.01318  -0.0570   0.0084   1.0000
   5.250   0.7460   0.02312   0.01557  -0.0563   0.0063   1.0000
   5.500   0.7707   0.02438   0.01709  -0.0556   0.0043   1.0000
   5.750   0.7943   0.02691   0.02002  -0.0543   0.0038   1.0000
   6.000   0.8149   0.03009   0.02368  -0.0523   0.0035   1.0000
   6.250   0.8318   0.03374   0.02782  -0.0498   0.0034   1.0000
   6.500   0.8452   0.03787   0.03241  -0.0470   0.0034   1.0000
   6.750   0.8556   0.04222   0.03720  -0.0440   0.0034   1.0000
   7.000   0.8631   0.04670   0.04204  -0.0410   0.0034   1.0000
   7.250   0.8679   0.05125   0.04692  -0.0383   0.0035   1.0000
   7.500   0.8697   0.05586   0.05181  -0.0356   0.0036   1.0000
   7.750   0.8686   0.06042   0.05661  -0.0333   0.0037   1.0000
   8.000   0.8641   0.06496   0.06135  -0.0312   0.0037   1.0000
   8.250   0.8567   0.06924   0.06579  -0.0294   0.0038   1.0000
   8.500   0.8436   0.07318   0.06984  -0.0273   0.0038   1.0000
   8.750   0.8287   0.07733   0.07408  -0.0263   0.0039   1.0000
   9.000   0.8138   0.08207   0.07889  -0.0272   0.0039   1.0000
   9.250   0.8006   0.08777   0.08464  -0.0304   0.0040   1.0000
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