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EPPLER 339 AIRFOIL (e339-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 339 AIRFOIL (e339-il)
Reynolds number: 50,000
Max Cl/Cd: 15.65 at α=-0.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e339-il-50000.txt
Download as CSV file: xf-e339-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 339 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2921   0.10682   0.10080  -0.0279   1.0000   0.2015
  -8.500  -0.2803   0.10271   0.09677  -0.0268   1.0000   0.2093
  -8.250  -0.2920   0.10118   0.09540  -0.0270   1.0000   0.2194
  -8.000  -0.2795   0.09733   0.09164  -0.0254   1.0000   0.2298
  -7.750  -0.3056   0.09662   0.09115  -0.0254   1.0000   0.2382
  -7.500  -0.2905   0.09290   0.08754  -0.0231   1.0000   0.2530
  -7.250  -0.2933   0.09039   0.08521  -0.0211   1.0000   0.2653
  -7.000  -0.3215   0.09002   0.08513  -0.0181   1.0000   0.2725
  -6.750  -0.3589   0.09079   0.08617  -0.0120   1.0000   0.2715
  -6.500  -0.3973   0.09190   0.08749  -0.0061   1.0000   0.2669
  -6.250  -0.4325   0.09176   0.08743  -0.0090   0.9904   0.2749
  -5.750  -0.3366   0.08252   0.07825  -0.0102   0.9680   0.3759
  -5.500  -0.2362   0.07834   0.07402  -0.0045   0.9644   0.5325
  -5.250  -0.0584   0.07021   0.06572  -0.0084   0.9657   0.7861
  -4.750   0.0075   0.06166   0.05710  -0.0240   0.9344   0.7794
  -4.500  -0.0759   0.06078   0.05633  -0.0259   0.9083   0.6391
  -4.250  -0.1366   0.05798   0.05360  -0.0287   0.8856   0.5681
  -4.000  -0.1839   0.05492   0.05044  -0.0336   0.8642   0.5068
  -3.750  -0.1581   0.04941   0.04279  -0.0571   0.8452   0.2374
  -3.500  -0.1119   0.04591   0.03825  -0.0591   0.8339   0.1625
  -3.250  -0.0856   0.04385   0.03564  -0.0582   0.8214   0.1408
  -3.000  -0.0369   0.04102   0.03209  -0.0599   0.8132   0.1243
  -2.750  -0.0188   0.04025   0.03082  -0.0577   0.7998   0.1180
  -2.500   0.0107   0.03902   0.02918  -0.0572   0.7891   0.1175
  -2.250   0.0487   0.03723   0.02720  -0.0580   0.7795   0.1207
  -2.000   0.3678   0.02670   0.01876  -0.0974   0.7719   1.0000
  -1.750   0.3890   0.02707   0.01868  -0.0962   0.7605   1.0000
  -1.500   0.4032   0.02781   0.01915  -0.0945   0.7486   1.0000
  -1.250   0.4254   0.02818   0.01917  -0.0935   0.7396   1.0000
  -1.000   0.4371   0.02911   0.01994  -0.0917   0.7285   1.0000
  -0.750   0.4565   0.02968   0.02026  -0.0904   0.7201   1.0000
  -0.500   0.4674   0.03072   0.02116  -0.0886   0.7102   1.0000
  -0.250   0.4890   0.03124   0.02145  -0.0875   0.7032   1.0000
   0.000   0.4922   0.03277   0.02294  -0.0851   0.6938   1.0000
   0.250   0.5153   0.03323   0.02319  -0.0841   0.6873   1.0000
   0.500   0.5118   0.03518   0.02514  -0.0811   0.6787   1.0000
   0.750   0.5260   0.03617   0.02600  -0.0795   0.6719   1.0000
   1.000   0.5350   0.03753   0.02726  -0.0774   0.6658   1.0000
   1.250   0.5201   0.04002   0.02976  -0.0732   0.6584   1.0000
   1.500   0.5394   0.04083   0.03045  -0.0720   0.6527   1.0000
   1.750   0.5272   0.04324   0.03283  -0.0681   0.6472   1.0000
   2.000   0.4868   0.04666   0.03629  -0.0615   0.6425   1.0000
   2.250   0.4689   0.04891   0.03850  -0.0567   0.6382   1.0000
   2.500   0.5288   0.04862   0.03802  -0.0598   0.6324   1.0000
   2.750   0.4662   0.05249   0.04192  -0.0508   0.6312   1.0000
   3.000   0.4342   0.05522   0.04462  -0.0453   0.6306   1.0000
   3.250   0.4166   0.05758   0.04694  -0.0416   0.6304   1.0000
   3.500   0.4101   0.05979   0.04910  -0.0391   0.6310   1.0000
   3.750   0.4130   0.06200   0.05125  -0.0378   0.6327   1.0000
   4.000   0.2263   0.06801   0.05769  -0.0274   0.7987   1.0000
   4.250   0.2367   0.06948   0.05906  -0.0265   0.7880   1.0000
   4.500   0.2684   0.07235   0.06179  -0.0285   0.7777   1.0000
   4.750   0.2722   0.07305   0.06241  -0.0264   0.7635   1.0000
   5.000   0.2850   0.07485   0.06413  -0.0259   0.7531   1.0000
   5.250   0.3123   0.07742   0.06662  -0.0272   0.7422   1.0000
   5.500   0.3145   0.07831   0.06746  -0.0253   0.7294   1.0000
   5.750   0.3425   0.08150   0.07056  -0.0268   0.7213   1.0000
   6.000   0.3510   0.08255   0.07158  -0.0256   0.7074   1.0000
   6.250   0.3559   0.08401   0.07300  -0.0244   0.6965   1.0000
   6.500   0.3895   0.08747   0.07641  -0.0264   0.6872   1.0000
   6.750   0.3860   0.08801   0.07694  -0.0242   0.6740   1.0000
   7.000   0.4112   0.09139   0.08028  -0.0254   0.6671   1.0000
   7.250   0.4172   0.09248   0.08136  -0.0243   0.6537   1.0000
   7.500   0.4219   0.09419   0.08306  -0.0233   0.6433   1.0000
   7.750   0.4521   0.09757   0.08645  -0.0248   0.6337   1.0000
   8.000   0.4465   0.09841   0.08729  -0.0230   0.6222   1.0000
   8.250   0.4853   0.10303   0.09192  -0.0254   0.6148   1.0000
   8.500   0.4733   0.10300   0.09189  -0.0230   0.6019   1.0000
   8.750   0.4928   0.10637   0.09529  -0.0238   0.5951   1.0000
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