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EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il)
Reynolds number: 50,000
Max Cl/Cd: 23.47 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e818-il-50000.txt
Download as CSV file: xf-e818-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 818 HYDROFOIL 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.5497   0.08413   0.07817  -0.0386   1.0000   0.1009
  -7.250  -0.5703   0.07620   0.07026  -0.0449   1.0000   0.0876
  -7.000  -0.5804   0.07036   0.06432  -0.0480   1.0000   0.0799
  -6.750  -0.5979   0.06254   0.05568  -0.0559   1.0000   0.0713
  -6.500  -0.5865   0.05827   0.05152  -0.0548   1.0000   0.0687
  -6.250  -0.5768   0.05323   0.04615  -0.0564   1.0000   0.0660
  -6.000  -0.5599   0.04762   0.03973  -0.0593   1.0000   0.0610
  -5.750  -0.5368   0.04351   0.03476  -0.0610   1.0000   0.0596
  -5.500  -0.5133   0.03992   0.03071  -0.0616   1.0000   0.0600
  -5.250  -0.4901   0.03688   0.02747  -0.0618   1.0000   0.0633
  -5.000  -0.4638   0.03429   0.02445  -0.0618   1.0000   0.0666
  -4.750  -0.4373   0.03206   0.02181  -0.0611   1.0000   0.0688
  -4.500  -0.4122   0.03023   0.01968  -0.0595   1.0000   0.0710
  -4.250  -0.3890   0.02824   0.01754  -0.0582   1.0000   0.0757
  -4.000  -0.3618   0.02645   0.01563  -0.0579   1.0000   0.0869
  -3.750  -0.3233   0.02291   0.01449  -0.0613   1.0000   0.4407
  -3.500  -0.3458   0.02717   0.01958  -0.0442   1.0000   0.5734
  -3.250  -0.3378   0.02764   0.01984  -0.0379   1.0000   0.6049
  -3.000  -0.3150   0.02705   0.01887  -0.0370   1.0000   0.6279
  -2.750  -0.2921   0.02649   0.01799  -0.0363   1.0000   0.6517
  -2.500  -0.2742   0.02605   0.01736  -0.0342   1.0000   0.6722
  -2.250  -0.2539   0.02558   0.01669  -0.0328   1.0000   0.6954
  -2.000  -0.2338   0.02514   0.01607  -0.0315   1.0000   0.7199
  -1.750  -0.2148   0.02472   0.01550  -0.0300   1.0000   0.7452
  -1.500  -0.1971   0.02432   0.01481  -0.0281   1.0000   0.7714
  -1.250  -0.1815   0.02391   0.01431  -0.0257   1.0000   0.7986
  -1.000  -0.1680   0.02345   0.01379  -0.0229   1.0000   0.8281
  -0.750  -0.1547   0.02295   0.01324  -0.0203   1.0000   0.8625
  -0.500  -0.1433   0.02231   0.01261  -0.0172   1.0000   0.9032
  -0.250  -0.1101   0.02160   0.01189  -0.0191   1.0000   0.9665
   0.000  -0.0704   0.02121   0.01133  -0.0248   1.0000   1.0000
   0.250  -0.0270   0.02141   0.01121  -0.0309   1.0000   1.0000
   0.500   0.0125   0.02172   0.01132  -0.0356   1.0000   1.0000
   0.750   0.0476   0.02210   0.01152  -0.0389   1.0000   1.0000
   1.000   0.0791   0.02251   0.01180  -0.0413   1.0000   1.0000
   1.250   0.1082   0.02295   0.01215  -0.0431   1.0000   1.0000
   1.500   0.1355   0.02342   0.01256  -0.0443   1.0000   1.0000
   1.750   0.1614   0.02393   0.01302  -0.0453   1.0000   1.0000
   2.000   0.1862   0.02447   0.01354  -0.0460   1.0000   1.0000
   2.250   0.2103   0.02505   0.01413  -0.0466   1.0000   1.0000
   2.500   0.2335   0.02566   0.01479  -0.0471   1.0000   1.0000
   2.750   0.2562   0.02632   0.01551  -0.0475   1.0000   1.0000
   3.000   0.2782   0.02703   0.01631  -0.0478   1.0000   1.0000
   3.250   0.2995   0.02779   0.01737  -0.0481   1.0000   1.0000
   3.500   0.3202   0.02861   0.01835  -0.0483   1.0000   1.0000
   3.750   0.3403   0.02950   0.01941  -0.0485   1.0000   1.0000
   4.000   0.3597   0.03046   0.02056  -0.0488   1.0000   1.0000
   4.250   0.3783   0.03151   0.02181  -0.0490   1.0000   1.0000
   4.500   0.3962   0.03265   0.02318  -0.0493   1.0000   1.0000
   4.750   0.4132   0.03391   0.02469  -0.0496   1.0000   1.0000
   5.000   0.4433   0.03573   0.02688  -0.0526   0.9924   1.0000
   5.250   0.5307   0.03828   0.03053  -0.0648   0.9447   1.0000
   5.500   0.8403   0.03581   0.02495  -0.0748   0.0693   1.0000
   5.750   0.8790   0.03940   0.02899  -0.0750   0.0700   1.0000
   6.000   0.9101   0.04325   0.03332  -0.0741   0.0726   1.0000
   6.250   0.9371   0.04778   0.03813  -0.0733   0.0757   1.0000
   6.500   0.9552   0.05101   0.04233  -0.0700   0.0835   1.0000
   6.750   0.9738   0.05534   0.04723  -0.0677   0.0929   1.0000
   7.000   0.9858   0.06019   0.05281  -0.0648   0.1085   1.0000
   7.250   0.9949   0.06573   0.05910  -0.0624   0.1347   1.0000
   7.500   0.9973   0.07326   0.06748  -0.0621   0.1910   1.0000
   7.750   0.9178   0.07208   0.06701  -0.0532   0.1921   1.0000
   8.000   0.8876   0.07784   0.07300  -0.0521   0.2045   1.0000
   8.250   0.8553   0.08252   0.07773  -0.0508   0.2030   1.0000
   8.500   0.8220   0.08883   0.08410  -0.0523   0.2104   1.0000
   8.750   0.7890   0.09598   0.09123  -0.0558   0.2122   1.0000
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