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EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il)
Reynolds number: 100,000
Max Cl/Cd: 40.94 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e818-il-100000-n5.txt
Download as CSV file: xf-e818-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4775   0.08822   0.08341  -0.0428   1.0000   0.0102
  -8.750  -0.4881   0.08424   0.07949  -0.0429   1.0000   0.0100
  -8.500  -0.5008   0.08006   0.07537  -0.0431   1.0000   0.0099
  -8.250  -0.5160   0.07596   0.07131  -0.0435   1.0000   0.0099
  -8.000  -0.5337   0.07228   0.06766  -0.0436   1.0000   0.0098
  -7.750  -0.5557   0.06912   0.06453  -0.0431   1.0000   0.0098
  -7.500  -0.5743   0.06543   0.06080  -0.0445   1.0000   0.0098
  -7.250  -0.5735   0.05926   0.05439  -0.0518   0.9960   0.0097
  -7.000  -0.5649   0.05350   0.04828  -0.0577   0.9918   0.0095
  -6.750  -0.5530   0.04843   0.04279  -0.0616   0.9881   0.0093
  -6.500  -0.5343   0.04375   0.03764  -0.0652   0.9850   0.0091
  -6.250  -0.5104   0.03943   0.03277  -0.0683   0.9827   0.0089
  -6.000  -0.4835   0.03589   0.02869  -0.0706   0.9811   0.0088
  -5.750  -0.4591   0.03287   0.02518  -0.0715   0.9792   0.0087
  -5.500  -0.4327   0.03034   0.02225  -0.0721   0.9774   0.0086
  -5.250  -0.4052   0.02818   0.01975  -0.0726   0.9756   0.0085
  -5.000  -0.3771   0.02633   0.01766  -0.0730   0.9741   0.0086
  -4.750  -0.3487   0.02476   0.01590  -0.0735   0.9727   0.0087
  -4.500  -0.3183   0.02340   0.01418  -0.0746   0.9713   0.0090
  -4.250  -0.2858   0.02230   0.01277  -0.0762   0.9700   0.0094
  -4.000  -0.2522   0.02142   0.01153  -0.0778   0.9688   0.0102
  -3.750  -0.2222   0.02048   0.01034  -0.0787   0.9670   0.0167
  -3.500  -0.1883   0.01796   0.01002  -0.0826   0.9668   0.4189
  -3.250  -0.1612   0.01795   0.00983  -0.0825   0.9641   0.4499
  -3.000  -0.1326   0.01792   0.00963  -0.0829   0.9617   0.4676
  -2.750  -0.1032   0.01793   0.00952  -0.0834   0.9595   0.4845
  -2.500  -0.0726   0.01796   0.00933  -0.0842   0.9575   0.5026
  -2.250  -0.0411   0.01803   0.00932  -0.0852   0.9558   0.5206
  -2.000  -0.0174   0.01804   0.00931  -0.0847   0.9524   0.5366
  -1.750   0.0097   0.01809   0.00934  -0.0848   0.9494   0.5540
  -1.250   0.0697   0.01826   0.00951  -0.0862   0.9445   0.5896
  -1.000   0.0991   0.01837   0.00957  -0.0868   0.9421   0.6077
  -0.750   0.1230   0.01845   0.00967  -0.0863   0.9379   0.6255
  -0.500   0.1511   0.01854   0.00982  -0.0865   0.9347   0.6431
  -0.250   0.1820   0.01865   0.00998  -0.0874   0.9320   0.6624
   0.000   0.2119   0.01876   0.01016  -0.0880   0.9291   0.6811
   0.250   0.2348   0.01887   0.01034  -0.0872   0.9242   0.6994
   0.500   0.2641   0.01897   0.01053  -0.0877   0.9206   0.7193
   0.750   0.2959   0.01906   0.01073  -0.0886   0.9179   0.7397
   1.000   0.3179   0.01917   0.01095  -0.0876   0.9123   0.7603
   1.250   0.3457   0.01924   0.01115  -0.0876   0.9078   0.7828
   1.750   0.3966   0.01931   0.01155  -0.0866   0.8973   0.8333
   2.000   0.4257   0.01925   0.01184  -0.0866   0.8929   0.8655
   2.250   0.4469   0.01919   0.01200  -0.0852   0.8858   0.9157
   2.500   0.4838   0.01908   0.01209  -0.0871   0.8804   1.0000
   2.750   0.5146   0.01919   0.01234  -0.0879   0.8728   1.0000
   3.750   0.6866   0.01677   0.00776  -0.0899   0.1823   1.0000
   4.000   0.6999   0.01935   0.00921  -0.0878   0.0245   1.0000
   4.250   0.7222   0.02043   0.01047  -0.0866   0.0184   1.0000
   4.500   0.7417   0.02185   0.01205  -0.0850   0.0162   1.0000
   4.750   0.7605   0.02389   0.01418  -0.0833   0.0150   1.0000
   5.000   0.7873   0.02570   0.01610  -0.0828   0.0144   1.0000
   5.250   0.8189   0.02792   0.01848  -0.0830   0.0138   1.0000
   5.500   0.8516   0.03056   0.02138  -0.0831   0.0134   1.0000
   5.750   0.8814   0.03352   0.02471  -0.0826   0.0132   1.0000
   6.000   0.9069   0.03636   0.02798  -0.0814   0.0125   1.0000
   6.250   0.9289   0.03884   0.03090  -0.0799   0.0106   1.0000
   6.500   0.9462   0.04078   0.03330  -0.0786   0.0082   1.0000
   6.750   0.9589   0.04330   0.03611  -0.0769   0.0071   1.0000
   7.000   0.9699   0.04687   0.04009  -0.0746   0.0068   1.0000
   7.250   0.9794   0.05048   0.04411  -0.0720   0.0069   1.0000
   7.500   0.9859   0.05423   0.04826  -0.0691   0.0070   1.0000
   7.750   0.9896   0.05813   0.05253  -0.0662   0.0071   1.0000
   8.000   0.9898   0.06223   0.05696  -0.0632   0.0073   1.0000
   8.250   0.9855   0.06652   0.06157  -0.0601   0.0076   1.0000
   8.500   0.9758   0.07072   0.06603  -0.0569   0.0078   1.0000
   8.750   0.9619   0.07470   0.07021  -0.0539   0.0080   1.0000
   9.000   0.9463   0.07887   0.07455  -0.0519   0.0082   1.0000
   9.250   0.9296   0.08343   0.07926  -0.0511   0.0083   1.0000
   9.500   0.9125   0.08860   0.08456  -0.0517   0.0085   1.0000
   9.750   0.8962   0.09455   0.09060  -0.0540   0.0086   1.0000
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