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EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il)
Reynolds number: 100,000
Max Cl/Cd: 40.89 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e817-il-100000.txt
Download as CSV file: xf-e817-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 817 HYDROFOIL AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5172   0.11352   0.10903  -0.0413   1.0000   0.1213
  -9.750  -0.5481   0.08797   0.08345  -0.0519   1.0000   0.0430
  -9.500  -0.5566   0.08451   0.08006  -0.0506   1.0000   0.0417
  -9.250  -0.5721   0.08034   0.07593  -0.0506   1.0000   0.0401
  -9.000  -0.5977   0.07554   0.07115  -0.0517   1.0000   0.0394
  -8.750  -0.6258   0.07171   0.06733  -0.0518   1.0000   0.0387
  -8.500  -0.6541   0.06906   0.06467  -0.0508   1.0000   0.0388
  -8.250  -0.6766   0.06503   0.06052  -0.0519   1.0000   0.0384
  -8.000  -0.6932   0.06037   0.05563  -0.0525   1.0000   0.0371
  -7.750  -0.7109   0.05352   0.04797  -0.0544   1.0000   0.0335
  -7.500  -0.6986   0.05154   0.04554  -0.0536   1.0000   0.0318
  -7.250  -0.6909   0.04631   0.04002  -0.0541   1.0000   0.0309
  -7.000  -0.6760   0.04356   0.03664  -0.0545   1.0000   0.0321
  -6.750  -0.6586   0.03926   0.03185  -0.0551   1.0000   0.0324
  -6.500  -0.6399   0.03522   0.02759  -0.0559   1.0000   0.0353
  -6.250  -0.6173   0.03281   0.02488  -0.0558   1.0000   0.0372
  -6.000  -0.5928   0.03029   0.02204  -0.0554   1.0000   0.0388
  -5.750  -0.5683   0.02822   0.01973  -0.0546   1.0000   0.0413
  -5.500  -0.5442   0.02593   0.01739  -0.0539   1.0000   0.0463
  -5.250  -0.5187   0.02417   0.01572  -0.0545   1.0000   0.0641
  -5.000  -0.4779   0.01959   0.01262  -0.0599   1.0000   0.2801
  -4.750  -0.4535   0.01999   0.01301  -0.0595   1.0000   0.3693
  -4.500  -0.4308   0.02038   0.01315  -0.0587   1.0000   0.4050
  -4.250  -0.4082   0.02064   0.01329  -0.0578   1.0000   0.4310
  -4.000  -0.3865   0.02090   0.01350  -0.0567   1.0000   0.4545
  -3.750  -0.3654   0.02115   0.01374  -0.0553   1.0000   0.4758
  -3.500  -0.3425   0.02129   0.01377  -0.0546   1.0000   0.4964
  -3.250  -0.3195   0.02130   0.01369  -0.0539   1.0000   0.5117
  -3.000  -0.2959   0.02126   0.01355  -0.0535   1.0000   0.5254
  -2.750  -0.2722   0.02122   0.01342  -0.0531   1.0000   0.5388
  -2.500  -0.2486   0.02120   0.01327  -0.0527   1.0000   0.5523
  -2.250  -0.2253   0.02121   0.01322  -0.0523   1.0000   0.5660
  -2.000  -0.2023   0.02124   0.01322  -0.0518   1.0000   0.5800
  -1.750  -0.1795   0.02130   0.01325  -0.0513   1.0000   0.5943
  -1.500  -0.1570   0.02138   0.01333  -0.0507   1.0000   0.6090
  -1.250  -0.1346   0.02149   0.01344  -0.0502   1.0000   0.6242
  -1.000  -0.1125   0.02162   0.01353  -0.0496   1.0000   0.6400
  -0.750  -0.0904   0.02178   0.01369  -0.0490   1.0000   0.6568
  -0.500  -0.0686   0.02196   0.01389  -0.0484   1.0000   0.6739
  -0.250  -0.0481   0.02216   0.01414  -0.0475   1.0000   0.6904
   0.000  -0.0275   0.02238   0.01441  -0.0467   1.0000   0.7084
   0.250  -0.0067   0.02262   0.01468  -0.0460   1.0000   0.7279
   0.500   0.0123   0.02287   0.01501  -0.0448   1.0000   0.7468
   0.750   0.0319   0.02315   0.01535  -0.0439   1.0000   0.7683
   1.000   0.0500   0.02343   0.01572  -0.0426   1.0000   0.7903
   1.250   0.0674   0.02372   0.01611  -0.0412   1.0000   0.8147
   1.500   0.1015   0.02446   0.01695  -0.0430   0.9917   0.8452
   1.750   0.1365   0.02518   0.01781  -0.0446   0.9817   0.8835
   2.000   0.1713   0.02527   0.01810  -0.0466   0.9700   0.9539
   2.250   0.2182   0.02578   0.01860  -0.0522   0.9581   1.0000
   2.500   0.2634   0.02643   0.01928  -0.0570   0.9469   1.0000
   2.750   0.3063   0.02706   0.01993  -0.0610   0.9357   1.0000
   3.000   0.3485   0.02767   0.02057  -0.0646   0.9246   1.0000
   3.250   0.3917   0.02823   0.02121  -0.0681   0.9137   1.0000
   3.500   0.4397   0.02874   0.02188  -0.0722   0.9035   1.0000
   3.750   0.4813   0.02898   0.02226  -0.0750   0.8905   1.0000
   4.000   0.5272   0.02903   0.02248  -0.0781   0.8770   1.0000
   4.250   0.5636   0.02883   0.02247  -0.0793   0.8592   1.0000
   4.500   0.6245   0.02764   0.02166  -0.0832   0.8403   1.0000
   4.750   0.6979   0.02471   0.01913  -0.0869   0.8142   1.0000
   5.000   0.7635   0.02095   0.01582  -0.0882   0.7825   1.0000
   5.250   0.7855   0.01921   0.01434  -0.0841   0.7371   1.0000
   5.500   0.8219   0.02077   0.01196  -0.0801   0.1279   1.0000
   5.750   0.8316   0.02315   0.01393  -0.0769   0.0792   1.0000
   6.000   0.8517   0.02537   0.01599  -0.0755   0.0552   1.0000
   6.250   0.8889   0.02824   0.01880  -0.0766   0.0445   1.0000
   6.500   0.9270   0.03143   0.02207  -0.0784   0.0371   1.0000
   6.750   0.9634   0.03443   0.02544  -0.0789   0.0359   1.0000
   7.000   0.9936   0.03796   0.02939  -0.0785   0.0359   1.0000
   7.250   1.0174   0.04199   0.03384  -0.0774   0.0366   1.0000
   7.500   1.0394   0.04701   0.03917  -0.0765   0.0380   1.0000
   7.750   1.0500   0.05003   0.04323  -0.0713   0.0444   1.0000
   8.000   1.0621   0.05627   0.04967  -0.0697   0.0490   1.0000
  11.000   0.8151   0.12224   0.11890  -0.0492   0.1142   1.0000
  11.250   0.7702   0.13077   0.12742  -0.0581   0.1139   1.0000
  11.500   0.7240   0.13738   0.13396  -0.0671   0.1090   1.0000
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