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EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il)
Reynolds number: 200,000
Max Cl/Cd: 56.39 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e818-il-200000.txt
Download as CSV file: xf-e818-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4988   0.09418   0.09098  -0.0350   1.0000   0.0406
  -8.500  -0.5101   0.09103   0.08788  -0.0346   1.0000   0.0414
  -8.250  -0.5233   0.08772   0.08463  -0.0343   1.0000   0.0422
  -8.000  -0.5382   0.08436   0.08133  -0.0340   1.0000   0.0426
  -7.750  -0.5566   0.08091   0.07795  -0.0336   1.0000   0.0427
  -7.500  -0.5777   0.07763   0.07473  -0.0328   1.0000   0.0424
  -7.250  -0.5953   0.07156   0.06867  -0.0375   1.0000   0.0418
  -6.250  -0.6034   0.04938   0.04552  -0.0528   1.0000   0.0487
  -6.000  -0.5884   0.04639   0.04244  -0.0535   1.0000   0.0523
  -5.000  -0.4465   0.02816   0.02149  -0.0637   0.9947   0.0227
  -4.750  -0.4132   0.02519   0.01830  -0.0649   0.9938   0.0184
  -4.500  -0.3806   0.02285   0.01556  -0.0656   0.9927   0.0161
  -4.250  -0.3490   0.02110   0.01362  -0.0661   0.9912   0.0146
  -4.000  -0.3164   0.01969   0.01210  -0.0671   0.9896   0.0137
  -3.750  -0.2820   0.01858   0.01084  -0.0687   0.9880   0.0134
  -3.500  -0.2472   0.01784   0.00986  -0.0705   0.9863   0.0139
  -3.250  -0.2121   0.01738   0.00912  -0.0721   0.9845   0.0161
  -3.000  -0.1730   0.01554   0.00837  -0.0759   0.9839   0.2801
  -2.750  -0.1390   0.01537   0.00876  -0.0778   0.9824   0.4378
  -2.500  -0.1086   0.01572   0.00924  -0.0785   0.9800   0.5064
  -2.250  -0.0823   0.01573   0.00918  -0.0785   0.9768   0.5273
  -2.000  -0.0524   0.01584   0.00927  -0.0793   0.9738   0.5465
  -1.750  -0.0205   0.01600   0.00945  -0.0804   0.9713   0.5646
  -1.500   0.0144   0.01626   0.00970  -0.0822   0.9691   0.5845
  -1.250   0.0399   0.01631   0.00980  -0.0820   0.9653   0.6014
  -1.000   0.0683   0.01642   0.00995  -0.0825   0.9616   0.6193
  -0.750   0.1012   0.01660   0.01012  -0.0838   0.9586   0.6388
  -0.500   0.1364   0.01684   0.01043  -0.0855   0.9563   0.6575
  -0.250   0.1599   0.01691   0.01056  -0.0850   0.9513   0.6761
   0.000   0.1900   0.01703   0.01077  -0.0857   0.9473   0.6952
   0.250   0.2255   0.01721   0.01103  -0.0874   0.9444   0.7160
   0.500   0.2520   0.01732   0.01125  -0.0874   0.9393   0.7352
   0.750   0.2821   0.01740   0.01142  -0.0880   0.9343   0.7565
   1.000   0.3184   0.01750   0.01165  -0.0897   0.9312   0.7777
   1.250   0.3413   0.01757   0.01185  -0.0889   0.9246   0.7998
   1.500   0.3736   0.01759   0.01201  -0.0897   0.9201   0.8242
   1.750   0.4120   0.01756   0.01216  -0.0916   0.9172   0.8505
   2.000   0.4289   0.01746   0.01234  -0.0892   0.9080   0.8831
   2.250   0.4673   0.01718   0.01228  -0.0907   0.9046   0.9343
   2.500   0.5009   0.01703   0.01226  -0.0922   0.8953   1.0000
   2.750   0.5564   0.01661   0.01201  -0.0972   0.8916   1.0000
   3.000   0.5983   0.01606   0.01163  -0.0993   0.8808   1.0000
   3.250   0.6795   0.01205   0.00514  -0.0992   0.2995   1.0000
   3.500   0.6801   0.01522   0.00686  -0.0948   0.0266   1.0000
   3.750   0.7031   0.01621   0.00801  -0.0937   0.0231   1.0000
   4.000   0.7244   0.01745   0.00932  -0.0923   0.0218   1.0000
   4.250   0.7476   0.01898   0.01089  -0.0911   0.0213   1.0000
   4.500   0.7772   0.02096   0.01292  -0.0908   0.0213   1.0000
   4.750   0.8085   0.02425   0.01628  -0.0917   0.0148   1.0000
   5.000   0.8375   0.02557   0.01782  -0.0912   0.0136   1.0000
   5.250   0.8679   0.02897   0.02157  -0.0907   0.0141   1.0000
   5.500   0.8978   0.03106   0.02385  -0.0900   0.0167   1.0000
   6.500   0.9803   0.04784   0.04261  -0.0792   0.0350   1.0000
   6.750   0.9917   0.05096   0.04617  -0.0766   0.0323   1.0000
   7.000   1.0009   0.05432   0.04976  -0.0744   0.0304   1.0000
   7.250   1.0087   0.05799   0.05355  -0.0727   0.0290   1.0000
   7.500   1.0157   0.06330   0.05887  -0.0718   0.0279   1.0000
   7.750   1.0026   0.07249   0.06827  -0.0696   0.0269   1.0000
   8.000   0.9998   0.07588   0.07193  -0.0667   0.0269   1.0000
   8.250   0.9938   0.07910   0.07540  -0.0639   0.0268   1.0000
   8.500   0.9844   0.08211   0.07864  -0.0610   0.0266   1.0000
   8.750   0.9700   0.08484   0.08155  -0.0578   0.0265   1.0000
   9.000   0.9533   0.08791   0.08476  -0.0552   0.0263   1.0000
   9.250   0.9364   0.09170   0.08867  -0.0541   0.0263   1.0000
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