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EPPLER 635 AIRFOIL (e635-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 635 AIRFOIL (e635-il)
Reynolds number: 50,000
Max Cl/Cd: 14.58 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e635-il-50000.txt
Download as CSV file: xf-e635-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 635 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  -0.4624   0.10364   0.09784   0.0166   1.0000   0.2614
  -8.500  -0.4585   0.10033   0.09460   0.0168   1.0000   0.2783
  -8.250  -0.4607   0.09750   0.09187   0.0168   1.0000   0.2971
  -8.000  -0.4464   0.09385   0.08829   0.0185   1.0000   0.3231
  -7.750  -0.4378   0.09077   0.08528   0.0204   1.0000   0.3546
  -7.500  -0.4302   0.08794   0.08255   0.0223   1.0000   0.3872
  -7.250  -0.4103   0.08456   0.07922   0.0251   1.0000   0.4285
  -7.000  -0.3912   0.08168   0.07639   0.0282   1.0000   0.4771
  -6.750  -0.3611   0.07844   0.07318   0.0314   1.0000   0.5366
  -6.500  -0.3314   0.07597   0.07076   0.0356   1.0000   0.6176
  -5.500  -0.3423   0.06219   0.05758   0.0304   1.0000   0.5778
  -5.250  -0.4182   0.05845   0.05426   0.0265   1.0000   0.5087
  -5.000  -0.4627   0.05748   0.05360   0.0297   1.0000   0.5000
  -4.750  -0.4692   0.04848   0.04192   0.0010   0.9678   0.1933
  -4.500  -0.4107   0.04265   0.03516  -0.0040   0.9478   0.1456
  -4.250  -0.3555   0.03855   0.03028  -0.0085   0.9288   0.1354
  -4.000  -0.3046   0.03574   0.02678  -0.0115   0.9085   0.1310
  -3.750  -0.2587   0.03311   0.02371  -0.0137   0.8874   0.1289
  -3.500  -0.2156   0.03126   0.02136  -0.0150   0.8673   0.1312
  -3.250  -0.1766   0.02955   0.01951  -0.0161   0.8464   0.1385
  -3.000   0.0970   0.02256   0.01507  -0.0476   0.8206   1.0000
  -2.750   0.1162   0.02281   0.01490  -0.0463   0.7991   1.0000
  -2.500   0.1350   0.02307   0.01480  -0.0449   0.7804   1.0000
  -2.250   0.1545   0.02336   0.01476  -0.0436   0.7638   1.0000
  -2.000   0.1748   0.02367   0.01480  -0.0426   0.7483   1.0000
  -1.750   0.1951   0.02401   0.01490  -0.0416   0.7338   1.0000
  -1.500   0.2161   0.02440   0.01506  -0.0409   0.7200   1.0000
  -1.250   0.2377   0.02484   0.01530  -0.0403   0.7071   1.0000
  -1.000   0.2592   0.02530   0.01559  -0.0396   0.6951   1.0000
  -0.750   0.2797   0.02576   0.01586  -0.0386   0.6844   1.0000
  -0.500   0.3013   0.02628   0.01623  -0.0380   0.6735   1.0000
  -0.250   0.3236   0.02693   0.01679  -0.0379   0.6626   1.0000
   0.000   0.3445   0.02752   0.01724  -0.0370   0.6533   1.0000
   0.250   0.3660   0.02819   0.01781  -0.0366   0.6438   1.0000
   0.500   0.3877   0.02905   0.01862  -0.0366   0.6343   1.0000
   0.750   0.4076   0.02963   0.01907  -0.0352   0.6267   1.0000
   1.000   0.4290   0.03078   0.02024  -0.0358   0.6171   1.0000
   1.250   0.4488   0.03147   0.02082  -0.0345   0.6102   1.0000
   1.500   0.4686   0.03282   0.02221  -0.0351   0.6010   1.0000
   1.750   0.4879   0.03369   0.02300  -0.0339   0.5944   1.0000
   2.000   0.5053   0.03532   0.02470  -0.0345   0.5862   1.0000
   2.250   0.5249   0.03600   0.02529  -0.0328   0.5806   1.0000
   2.500   0.5376   0.03831   0.02771  -0.0339   0.5721   1.0000
   2.750   0.5563   0.03920   0.02855  -0.0324   0.5664   1.0000
   3.000   0.5633   0.04197   0.03141  -0.0332   0.5597   1.0000
   3.250   0.5762   0.04362   0.03307  -0.0323   0.5537   1.0000
   3.500   0.5873   0.04550   0.03498  -0.0315   0.5484   1.0000
   3.750   0.5801   0.04911   0.03864  -0.0315   0.5441   1.0000
   4.000   0.5805   0.05171   0.04125  -0.0306   0.5400   1.0000
   4.250   0.6022   0.05274   0.04226  -0.0291   0.5348   1.0000
   4.500   0.5838   0.05674   0.04627  -0.0283   0.5337   1.0000
   4.750   0.5734   0.06009   0.04960  -0.0271   0.5342   1.0000
   5.000   0.5655   0.06317   0.05267  -0.0258   0.5355   1.0000
   5.250   0.3651   0.07226   0.06158  -0.0219   0.7072   1.0000
   5.500   0.3767   0.07422   0.06352  -0.0211   0.6949   1.0000
   5.750   0.3921   0.07642   0.06571  -0.0208   0.6828   1.0000
   6.000   0.4115   0.07890   0.06821  -0.0209   0.6699   1.0000
   6.250   0.4332   0.08152   0.07085  -0.0212   0.6566   1.0000
   6.500   0.4356   0.08283   0.07214  -0.0194   0.6431   1.0000
   6.750   0.4420   0.08458   0.07389  -0.0181   0.6296   1.0000
   7.000   0.4489   0.08648   0.07579  -0.0170   0.6170   1.0000
   7.250   0.4595   0.08878   0.07810  -0.0165   0.6061   1.0000
   7.500   0.4901   0.09254   0.08194  -0.0176   0.5957   1.0000
   7.750   0.4922   0.09392   0.08334  -0.0161   0.5820   1.0000
   8.000   0.4929   0.09553   0.08495  -0.0148   0.5693   1.0000
   8.250   0.4974   0.09770   0.08715  -0.0139   0.5586   1.0000
   8.500   0.5172   0.10099   0.09049  -0.0142   0.5489   1.0000
   8.750   0.5341   0.10377   0.09336  -0.0140   0.5359   1.0000
   9.000   0.5281   0.10506   0.09466  -0.0126   0.5240   1.0000
   9.250   0.5318   0.10747   0.09710  -0.0121   0.5141   1.0000
   9.500   0.5516   0.11101   0.10071  -0.0123   0.5038   1.0000
   9.750   0.5635   0.11361   0.10338  -0.0119   0.4911   1.0000
  10.000   0.5555   0.11515   0.10493  -0.0110   0.4809   1.0000
  10.250   0.5654   0.11825   0.10809  -0.0109   0.4717   1.0000
  10.500   0.5944   0.12278   0.11277  -0.0114   0.4601   1.0000
  10.750   0.4516   0.11973   0.11034   0.0000   0.4427   1.0000
  11.000   0.4588   0.12223   0.11291   0.0003   0.4323   1.0000
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