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EPPLER 817 HYDROFOIL AIRFOIL (e817-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 817 HYDROFOIL AIRFOIL (e817-il)
Reynolds number: 50,000
Max Cl/Cd: 26.86 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e817-il-50000.txt
Download as CSV file: xf-e817-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5775   0.08814   0.08203  -0.0506   1.0000   0.0946
  -8.750  -0.5884   0.08449   0.07846  -0.0495   1.0000   0.0938
  -8.500  -0.5999   0.08102   0.07506  -0.0482   1.0000   0.0916
  -8.250  -0.6683   0.07329   0.06707  -0.0546   1.0000   0.0817
  -8.000  -0.6693   0.06899   0.06277  -0.0538   1.0000   0.0803
  -7.750  -0.6764   0.06442   0.05804  -0.0540   1.0000   0.0790
  -7.500  -0.6812   0.05947   0.05281  -0.0548   1.0000   0.0779
  -7.250  -0.6793   0.05461   0.04752  -0.0557   1.0000   0.0770
  -7.000  -0.6713   0.04993   0.04225  -0.0568   1.0000   0.0791
  -6.750  -0.6561   0.04577   0.03737  -0.0578   1.0000   0.0810
  -6.500  -0.6373   0.04173   0.03293  -0.0582   1.0000   0.0845
  -6.250  -0.6151   0.03851   0.02942  -0.0578   1.0000   0.0882
  -6.000  -0.5898   0.03547   0.02579  -0.0572   1.0000   0.0942
  -5.750  -0.5679   0.03277   0.02318  -0.0565   1.0000   0.1117
  -5.500  -0.5448   0.03014   0.02069  -0.0555   1.0000   0.1384
  -5.250  -0.5187   0.02741   0.01873  -0.0563   1.0000   0.2199
  -5.000  -0.5019   0.02831   0.02074  -0.0523   1.0000   0.3964
  -4.750  -0.4911   0.02996   0.02244  -0.0465   1.0000   0.4478
  -4.500  -0.4799   0.03118   0.02361  -0.0410   1.0000   0.4858
  -4.250  -0.4701   0.03215   0.02441  -0.0353   1.0000   0.5150
  -4.000  -0.4577   0.03261   0.02476  -0.0307   1.0000   0.5418
  -3.750  -0.4405   0.03247   0.02443  -0.0282   1.0000   0.5661
  -3.500  -0.4243   0.03224   0.02404  -0.0253   1.0000   0.5843
  -3.250  -0.4017   0.03159   0.02315  -0.0250   1.0000   0.6037
  -3.000  -0.3797   0.03098   0.02232  -0.0244   1.0000   0.6202
  -2.750  -0.3591   0.03044   0.02162  -0.0234   1.0000   0.6357
  -2.500  -0.3375   0.02990   0.02091  -0.0228   1.0000   0.6513
  -2.250  -0.3152   0.02939   0.02023  -0.0224   1.0000   0.6678
  -2.000  -0.2905   0.02886   0.01943  -0.0228   1.0000   0.6862
  -1.750  -0.2715   0.02846   0.01894  -0.0215   1.0000   0.7023
  -1.500  -0.2522   0.02808   0.01847  -0.0203   1.0000   0.7197
  -1.250  -0.2296   0.02771   0.01798  -0.0201   1.0000   0.7399
  -1.000  -0.2121   0.02738   0.01760  -0.0184   1.0000   0.7585
  -0.750  -0.1914   0.02708   0.01721  -0.0178   1.0000   0.7809
  -0.500  -0.1757   0.02675   0.01680  -0.0157   1.0000   0.8023
  -0.250  -0.1594   0.02642   0.01645  -0.0140   1.0000   0.8269
   0.000  -0.1446   0.02606   0.01608  -0.0119   1.0000   0.8546
   0.250  -0.1304   0.02564   0.01567  -0.0098   1.0000   0.8876
   0.500  -0.1124   0.02511   0.01521  -0.0085   1.0000   0.9303
   0.750  -0.0765   0.02438   0.01451  -0.0123   1.0000   1.0000
   1.000  -0.0353   0.02461   0.01458  -0.0185   1.0000   1.0000
   1.250   0.0052   0.02504   0.01487  -0.0240   1.0000   1.0000
   1.500   0.0423   0.02557   0.01528  -0.0283   1.0000   1.0000
   1.750   0.0756   0.02616   0.01577  -0.0316   1.0000   1.0000
   2.000   0.1055   0.02678   0.01631  -0.0340   1.0000   1.0000
   2.250   0.1330   0.02744   0.01691  -0.0358   1.0000   1.0000
   2.500   0.1587   0.02814   0.01758  -0.0371   1.0000   1.0000
   2.750   0.1829   0.02888   0.01831  -0.0381   1.0000   1.0000
   3.000   0.2061   0.02966   0.01917  -0.0390   1.0000   1.0000
   3.250   0.2282   0.03050   0.02004  -0.0397   1.0000   1.0000
   3.500   0.2495   0.03140   0.02100  -0.0403   1.0000   1.0000
   3.750   0.2699   0.03236   0.02204  -0.0408   1.0000   1.0000
   4.000   0.2896   0.03339   0.02316  -0.0414   1.0000   1.0000
   4.250   0.3085   0.03450   0.02438  -0.0418   1.0000   1.0000
   4.500   0.3265   0.03569   0.02577  -0.0423   1.0000   1.0000
   4.750   0.3438   0.03698   0.02720  -0.0428   1.0000   1.0000
   5.000   0.4022   0.03967   0.03022  -0.0510   0.9737   1.0000
   5.250   0.4689   0.04178   0.03275  -0.0593   0.9352   1.0000
   5.500   0.5306   0.04302   0.03457  -0.0657   0.8969   1.0000
   5.750   0.6133   0.04275   0.03499  -0.0726   0.8484   1.0000
   6.000   0.7573   0.03230   0.02603  -0.0745   0.7385   1.0000
   6.250   0.8037   0.02992   0.01977  -0.0611   0.1740   1.0000
   6.500   0.9105   0.03636   0.02561  -0.0711   0.1006   1.0000
   6.750   0.9455   0.03959   0.02914  -0.0715   0.0857   1.0000
   7.000   0.9776   0.04316   0.03323  -0.0710   0.0806   1.0000
   7.250   1.0039   0.04718   0.03779  -0.0698   0.0803   1.0000
   7.500   1.0227   0.05140   0.04259  -0.0676   0.0820   1.0000
   7.750   1.0364   0.05580   0.04748  -0.0653   0.0846   1.0000
   8.000   1.0502   0.06065   0.05263  -0.0635   0.0870   1.0000
   8.250   1.0465   0.06443   0.05725  -0.0591   0.0931   1.0000
   8.500   1.0466   0.06934   0.06254  -0.0564   0.0979   1.0000
   8.750   1.0367   0.07404   0.06777  -0.0530   0.1066   1.0000
   9.000   1.0285   0.07939   0.07348  -0.0507   0.1175   1.0000
   9.250   1.0250   0.08742   0.08176  -0.0502   0.1399   1.0000
   9.500   0.9744   0.09009   0.08473  -0.0468   0.1439   1.0000
   9.750   0.9374   0.09540   0.09014  -0.0471   0.1476   1.0000
  10.000   0.9045   0.10427   0.09911  -0.0522   0.1700   1.0000
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