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EPPLER 479 AIRFOIL (e479-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 479 AIRFOIL (e479-il)
Reynolds number: 50,000
Max Cl/Cd: 15.93 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e479-il-50000.txt
Download as CSV file: xf-e479-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 479 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4152   0.11252   0.10364   0.0180   1.0000   0.4580
  -9.500  -0.3962   0.10855   0.09964   0.0174   1.0000   0.4655
  -9.250  -0.4143   0.10805   0.09917   0.0183   1.0000   0.4770
  -9.000  -0.3756   0.10317   0.09424   0.0172   1.0000   0.4883
  -8.750  -0.3726   0.10067   0.09175   0.0174   1.0000   0.4985
  -8.500  -0.3781   0.09943   0.09053   0.0182   1.0000   0.5116
  -8.250  -0.3459   0.09513   0.08618   0.0171   1.0000   0.5211
  -8.000  -0.3439   0.09296   0.08403   0.0176   1.0000   0.5332
  -7.750  -0.4399   0.08183   0.07292   0.0090   1.0000   0.4264
  -7.500  -0.4434   0.07755   0.06863   0.0078   1.0000   0.4224
  -7.250  -0.4579   0.07320   0.06432   0.0070   1.0000   0.4231
  -7.000  -0.4295   0.07187   0.06297   0.0078   1.0000   0.4334
  -6.750  -0.4412   0.06798   0.05911   0.0075   1.0000   0.4357
  -6.500  -0.4706   0.06321   0.05443   0.0076   1.0000   0.4388
  -6.250  -0.5530   0.05466   0.04601   0.0083   1.0000   0.4418
  -6.000  -0.4850   0.05711   0.04844   0.0099   1.0000   0.4523
  -5.750  -0.5587   0.04932   0.04071   0.0114   1.0000   0.4586
  -5.500  -0.5159   0.05018   0.04163   0.0130   1.0000   0.4676
  -5.250  -0.5646   0.04478   0.03623   0.0157   1.0000   0.4763
  -5.000  -0.5359   0.04496   0.03650   0.0176   1.0000   0.4842
  -4.750  -0.5667   0.04164   0.03315   0.0212   1.0000   0.4933
  -4.500  -0.5597   0.04115   0.03276   0.0243   1.0000   0.5004
  -4.250  -0.5741   0.03948   0.03105   0.0277   1.0000   0.5087
  -4.000  -0.5797   0.03830   0.02987   0.0305   1.0000   0.5163
  -3.750  -0.5808   0.03748   0.02905   0.0329   1.0000   0.5250
  -3.500  -0.5811   0.03648   0.02801   0.0348   1.0000   0.5337
  -3.250  -0.5551   0.03556   0.02695   0.0318   0.9906   0.5471
  -3.000  -0.4874   0.03568   0.02710   0.0242   0.9678   0.5627
  -2.750  -0.4278   0.03554   0.02697   0.0182   0.9446   0.5769
  -2.500  -0.3668   0.03522   0.02663   0.0120   0.9232   0.5923
  -2.250  -0.3012   0.03475   0.02614   0.0054   0.9035   0.6082
  -2.000  -0.2457   0.03422   0.02558   0.0006   0.8836   0.6237
  -1.750  -0.2088   0.03360   0.02491  -0.0014   0.8620   0.6382
  -1.500  -0.1691   0.03327   0.02455  -0.0030   0.8418   0.6525
  -1.250  -0.1292   0.03312   0.02442  -0.0039   0.8223   0.6651
  -1.000  -0.0991   0.03282   0.02410  -0.0038   0.8035   0.6787
  -0.750  -0.0752   0.03253   0.02377  -0.0031   0.7857   0.6931
  -0.500  -0.0539   0.03230   0.02350  -0.0020   0.7686   0.7081
  -0.250  -0.0251   0.03237   0.02360  -0.0011   0.7518   0.7215
   0.000   0.0000   0.03239   0.02362   0.0000   0.7361   0.7362
   0.250   0.0251   0.03237   0.02360   0.0011   0.7216   0.7517
   0.500   0.0539   0.03230   0.02350   0.0020   0.7081   0.7686
   0.750   0.0752   0.03253   0.02377   0.0031   0.6931   0.7856
   1.000   0.0991   0.03282   0.02410   0.0038   0.6786   0.8035
   1.250   0.1293   0.03312   0.02442   0.0039   0.6650   0.8224
   1.500   0.1692   0.03327   0.02455   0.0030   0.6526   0.8418
   1.750   0.2087   0.03361   0.02491   0.0014   0.6383   0.8620
   2.000   0.2456   0.03422   0.02557  -0.0006   0.6237   0.8837
   2.250   0.3010   0.03475   0.02614  -0.0054   0.6083   0.9035
   2.500   0.3668   0.03522   0.02663  -0.0120   0.5923   0.9232
   2.750   0.4278   0.03553   0.02696  -0.0182   0.5768   0.9446
   3.000   0.4875   0.03568   0.02709  -0.0242   0.5626   0.9679
   3.250   0.5551   0.03554   0.02693  -0.0318   0.5471   0.9906
   3.500   0.5811   0.03647   0.02800  -0.0348   0.5337   1.0000
   3.750   0.5807   0.03747   0.02904  -0.0329   0.5251   1.0000
   4.000   0.5794   0.03831   0.02988  -0.0305   0.5163   1.0000
   4.250   0.5741   0.03947   0.03104  -0.0276   0.5087   1.0000
   4.500   0.5592   0.04118   0.03278  -0.0243   0.5005   1.0000
   4.750   0.5666   0.04164   0.03315  -0.0212   0.4933   1.0000
   5.000   0.5358   0.04497   0.03651  -0.0176   0.4842   1.0000
   5.250   0.5648   0.04476   0.03620  -0.0157   0.4763   1.0000
   5.500   0.5157   0.05020   0.04164  -0.0130   0.4676   1.0000
   5.750   0.5591   0.04930   0.04069  -0.0114   0.4586   1.0000
   6.000   0.4856   0.05707   0.04840  -0.0100   0.4522   1.0000
   6.250   0.5539   0.05460   0.04594  -0.0083   0.4418   1.0000
   6.500   0.4711   0.06319   0.05441  -0.0077   0.4388   1.0000
   6.750   0.4418   0.06795   0.05909  -0.0076   0.4357   1.0000
   7.000   0.4300   0.07187   0.06297  -0.0079   0.4334   1.0000
   7.250   0.4582   0.07320   0.06431  -0.0071   0.4230   1.0000
   7.500   0.4441   0.07753   0.06861  -0.0078   0.4224   1.0000
   7.750   0.4414   0.08178   0.07286  -0.0091   0.4263   1.0000
   8.000   0.4534   0.08534   0.07645  -0.0097   0.4250   1.0000
   8.250   0.3468   0.09512   0.08617  -0.0172   0.5210   1.0000
   8.500   0.3780   0.09937   0.09045  -0.0183   0.5115   1.0000
   8.750   0.3731   0.10064   0.09171  -0.0175   0.4987   1.0000
   9.000   0.3765   0.10317   0.09424  -0.0174   0.4883   1.0000
   9.250   0.4150   0.10802   0.09914  -0.0184   0.4770   1.0000
   9.500   0.3971   0.10855   0.09964  -0.0176   0.4655   1.0000
   9.750   0.4164   0.11254   0.10365  -0.0182   0.4580   1.0000
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