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EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il)
Reynolds number: 100,000
Max Cl/Cd: 47.25 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e817-il-100000-n5.txt
Download as CSV file: xf-e817-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5067   0.09588   0.09095  -0.0501   1.0000   0.0107
 -10.750  -0.5209   0.09085   0.08598  -0.0508   1.0000   0.0102
 -10.500  -0.5390   0.08506   0.08021  -0.0523   1.0000   0.0101
 -10.250  -0.5608   0.07919   0.07445  -0.0540   1.0000   0.0100
 -10.000  -0.5789   0.07481   0.07007  -0.0549   1.0000   0.0098
  -9.750  -0.6016   0.07018   0.06541  -0.0558   1.0000   0.0097
  -9.500  -0.6236   0.06631   0.06151  -0.0562   1.0000   0.0096
  -9.250  -0.6462   0.06305   0.05821  -0.0558   1.0000   0.0095
  -9.000  -0.6609   0.05817   0.05314  -0.0604   0.9950   0.0095
  -8.750  -0.6681   0.05340   0.04807  -0.0649   0.9896   0.0095
  -8.500  -0.6659   0.04896   0.04324  -0.0680   0.9848   0.0094
  -8.250  -0.6550   0.04459   0.03839  -0.0710   0.9814   0.0095
  -8.000  -0.6458   0.04126   0.03465  -0.0714   0.9777   0.0098
  -7.750  -0.6299   0.03866   0.03153  -0.0718   0.9749   0.0104
  -7.500  -0.6129   0.03534   0.02780  -0.0727   0.9725   0.0117
  -7.250  -0.5909   0.03310   0.02533  -0.0738   0.9705   0.0132
  -7.000  -0.5654   0.03131   0.02331  -0.0748   0.9689   0.0156
  -6.750  -0.5452   0.02956   0.02136  -0.0742   0.9668   0.0165
  -6.500  -0.5244   0.02794   0.01955  -0.0737   0.9647   0.0182
  -6.250  -0.5006   0.02654   0.01791  -0.0739   0.9626   0.0202
  -6.000  -0.4743   0.02498   0.01624  -0.0751   0.9607   0.0295
  -5.750  -0.4450   0.02324   0.01445  -0.0769   0.9592   0.0510
  -5.500  -0.4149   0.02124   0.01285  -0.0794   0.9581   0.1226
  -5.250  -0.3848   0.02009   0.01230  -0.0816   0.9571   0.2584
  -5.000  -0.3537   0.01994   0.01200  -0.0828   0.9558   0.3121
  -4.750  -0.3301   0.01985   0.01183  -0.0824   0.9531   0.3424
  -4.500  -0.3040   0.01985   0.01172  -0.0824   0.9507   0.3718
  -4.250  -0.2769   0.01990   0.01170  -0.0826   0.9486   0.3973
  -4.000  -0.2477   0.01991   0.01156  -0.0832   0.9466   0.4165
  -3.750  -0.2176   0.01988   0.01141  -0.0839   0.9449   0.4299
  -3.500  -0.1869   0.01988   0.01130  -0.0848   0.9434   0.4421
  -3.250  -0.1618   0.01986   0.01115  -0.0846   0.9408   0.4533
  -3.000  -0.1370   0.01985   0.01107  -0.0843   0.9380   0.4648
  -2.750  -0.1096   0.01986   0.01103  -0.0845   0.9355   0.4769
  -2.500  -0.0803   0.01990   0.01101  -0.0851   0.9333   0.4894
  -2.250  -0.0497   0.01995   0.01102  -0.0859   0.9314   0.5025
  -2.000  -0.0177   0.02002   0.01106  -0.0870   0.9297   0.5159
  -1.750   0.0025   0.02008   0.01107  -0.0859   0.9256   0.5282
  -1.500   0.0292   0.02016   0.01115  -0.0859   0.9225   0.5413
  -1.250   0.0585   0.02024   0.01125  -0.0865   0.9200   0.5552
  -1.000   0.0900   0.02034   0.01136  -0.0874   0.9178   0.5694
  -0.750   0.1164   0.02045   0.01149  -0.0874   0.9147   0.5834
  -0.500   0.1398   0.02057   0.01165  -0.0868   0.9104   0.5973
  -0.250   0.1688   0.02068   0.01181  -0.0873   0.9073   0.6120
   0.000   0.2006   0.02078   0.01197  -0.0883   0.9048   0.6278
   0.250   0.2260   0.02092   0.01218  -0.0880   0.9008   0.6428
   0.500   0.2507   0.02105   0.01239  -0.0877   0.8960   0.6584
   0.750   0.2816   0.02115   0.01258  -0.0884   0.8928   0.6744
   1.250   0.3340   0.02139   0.01303  -0.0880   0.8833   0.7069
   1.500   0.3656   0.02144   0.01324  -0.0887   0.8795   0.7247
   1.750   0.3952   0.02150   0.01344  -0.0890   0.8753   0.7425
   2.000   0.4176   0.02160   0.01368  -0.0880   0.8685   0.7606
   2.250   0.4516   0.02155   0.01379  -0.0890   0.8649   0.7809
   2.500   0.4712   0.02162   0.01404  -0.0874   0.8567   0.8013
   2.750   0.5043   0.02143   0.01410  -0.0880   0.8521   0.8244
   3.000   0.5242   0.02138   0.01424  -0.0862   0.8430   0.8510
   3.250   0.5584   0.02097   0.01406  -0.0866   0.8380   0.8832
   3.500   0.5827   0.02066   0.01399  -0.0855   0.8272   0.9461
   3.750   0.6165   0.02022   0.01373  -0.0862   0.8155   1.0000
   4.000   0.6551   0.01938   0.01315  -0.0870   0.8009   1.0000
   4.250   0.6840   0.01845   0.01237  -0.0858   0.7764   1.0000
   4.500   0.7047   0.01788   0.01195  -0.0835   0.7425   1.0000
   4.750   0.7318   0.01712   0.01128  -0.0819   0.6859   1.0000
   5.000   0.8000   0.01693   0.00929  -0.0858   0.3537   1.0000
   5.250   0.8073   0.01900   0.01022  -0.0830   0.1714   1.0000
   5.500   0.8222   0.02068   0.01129  -0.0814   0.0858   1.0000
   5.750   0.8380   0.02219   0.01251  -0.0796   0.0501   1.0000
   6.000   0.8555   0.02349   0.01381  -0.0779   0.0324   1.0000
   6.250   0.8709   0.02508   0.01554  -0.0760   0.0252   1.0000
   6.500   0.8901   0.02649   0.01712  -0.0744   0.0210   1.0000
   6.750   0.9101   0.02785   0.01851  -0.0735   0.0166   1.0000
   7.000   0.9355   0.03020   0.02099  -0.0732   0.0147   1.0000
   7.250   0.9664   0.03259   0.02363  -0.0736   0.0139   1.0000
   7.500   0.9968   0.03539   0.02675  -0.0737   0.0132   1.0000
   7.750   1.0226   0.03847   0.03023  -0.0732   0.0129   1.0000
   8.000   1.0423   0.04175   0.03396  -0.0718   0.0126   1.0000
   8.250   1.0558   0.04519   0.03786  -0.0696   0.0125   1.0000
   8.500   1.0640   0.04876   0.04188  -0.0669   0.0125   1.0000
   8.750   1.0669   0.05240   0.04594  -0.0637   0.0125   1.0000
   9.000   1.0651   0.05605   0.04998  -0.0603   0.0125   1.0000
   9.250   1.0578   0.05953   0.05379  -0.0565   0.0125   1.0000
   9.500   1.0466   0.06299   0.05754  -0.0526   0.0126   1.0000
   9.750   1.0325   0.06662   0.06143  -0.0492   0.0127   1.0000
  10.000   1.0163   0.07049   0.06555  -0.0464   0.0127   1.0000
  10.250   0.9986   0.07468   0.06995  -0.0445   0.0128   1.0000
  10.500   0.9795   0.07932   0.07479  -0.0437   0.0129   1.0000
  10.750   0.9597   0.08451   0.08016  -0.0441   0.0130   1.0000
  11.000   0.9394   0.09046   0.08626  -0.0459   0.0131   1.0000
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