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EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 639 AIRFOIL (e639-il)
Reynolds number: 50,000
Max Cl/Cd: 25.54 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e639-il-50000-n5.txt
Download as CSV file: xf-e639-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 639 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2762   0.10175   0.09589  -0.0325   1.0000   0.1114
  -8.250  -0.2969   0.10066   0.09502  -0.0349   1.0000   0.1125
  -8.000  -0.3163   0.09943   0.09399  -0.0359   1.0000   0.1129
  -7.750  -0.2783   0.09302   0.08762  -0.0319   1.0000   0.1172
  -7.500  -0.2841   0.09102   0.08581  -0.0307   1.0000   0.1198
  -7.250  -0.2838   0.08781   0.08262  -0.0417   0.9471   0.1279
  -7.000  -0.2514   0.08230   0.07713  -0.0430   0.9244   0.1340
  -6.750  -0.2358   0.07796   0.07265  -0.0515   0.8938   0.1461
  -6.500  -0.2180   0.07427   0.06879  -0.0567   0.8686   0.1610
  -6.250  -0.1964   0.07066   0.06507  -0.0580   0.8454   0.1741
  -6.000  -0.1774   0.06685   0.06118  -0.0583   0.8246   0.1833
  -5.750  -0.1669   0.06403   0.05823  -0.0588   0.8043   0.1983
  -5.500  -0.1376   0.05577   0.04864  -0.0669   0.7905   0.0672
  -5.250  -0.1217   0.05256   0.04535  -0.0664   0.7738   0.0647
  -5.000  -0.1060   0.04971   0.04222  -0.0658   0.7586   0.0620
  -4.750  -0.0892   0.04692   0.03902  -0.0650   0.7451   0.0593
  -4.500  -0.0714   0.04428   0.03588  -0.0639   0.7317   0.0570
  -4.250  -0.0527   0.04219   0.03341  -0.0628   0.7186   0.0573
  -4.000  -0.0329   0.04030   0.03119  -0.0618   0.7062   0.0582
  -3.750  -0.0116   0.03843   0.02892  -0.0606   0.6951   0.0586
  -3.500   0.0112   0.03662   0.02666  -0.0595   0.6846   0.0580
  -3.250   0.0344   0.03497   0.02459  -0.0584   0.6734   0.0575
  -3.000   0.0591   0.03347   0.02267  -0.0574   0.6633   0.0573
  -2.750   0.0852   0.03210   0.02093  -0.0565   0.6541   0.0575
  -2.500   0.1113   0.03095   0.01949  -0.0559   0.6440   0.0581
  -2.250   0.1393   0.02994   0.01822  -0.0554   0.6355   0.0606
  -2.000   0.1675   0.02911   0.01714  -0.0551   0.6260   0.0640
  -1.750   0.1986   0.02832   0.01608  -0.0550   0.6176   0.0666
  -1.500   0.2309   0.02754   0.01508  -0.0552   0.6093   0.0688
  -1.250   0.2584   0.02691   0.01435  -0.0549   0.6013   0.0723
  -1.000   0.2836   0.02649   0.01376  -0.0541   0.5939   0.0785
  -0.750   0.3073   0.02615   0.01333  -0.0533   0.5867   0.0882
  -0.500   0.4288   0.02237   0.01211  -0.0697   0.5768   1.0000
  -0.250   0.4497   0.02271   0.01212  -0.0685   0.5693   1.0000
   0.000   0.4716   0.02299   0.01207  -0.0674   0.5631   1.0000
   0.250   0.4928   0.02334   0.01218  -0.0663   0.5569   1.0000
   0.500   0.5134   0.02372   0.01237  -0.0652   0.5503   1.0000
   0.750   0.5361   0.02400   0.01237  -0.0642   0.5454   1.0000
   1.000   0.5551   0.02453   0.01281  -0.0630   0.5386   1.0000
   1.250   0.5763   0.02492   0.01303  -0.0620   0.5332   1.0000
   1.500   0.5985   0.02529   0.01321  -0.0610   0.5286   1.0000
   1.750   0.6164   0.02592   0.01381  -0.0597   0.5221   1.0000
   2.000   0.6378   0.02634   0.01409  -0.0586   0.5173   1.0000
   2.250   0.6590   0.02680   0.01443  -0.0576   0.5128   1.0000
   2.500   0.6759   0.02755   0.01518  -0.0563   0.5067   1.0000
   2.750   0.6970   0.02803   0.01556  -0.0552   0.5022   1.0000
   3.000   0.7191   0.02848   0.01589  -0.0543   0.4983   1.0000
   3.250   0.7330   0.02945   0.01693  -0.0527   0.4922   1.0000
   3.500   0.7530   0.03003   0.01747  -0.0516   0.4878   1.0000
   3.750   0.7766   0.03041   0.01774  -0.0508   0.4844   1.0000
   4.000   0.7871   0.03165   0.01908  -0.0490   0.4785   1.0000
   4.250   0.8044   0.03243   0.01986  -0.0477   0.4737   1.0000
   4.500   0.8273   0.03288   0.02027  -0.0469   0.4702   1.0000
   4.750   0.8385   0.03412   0.02159  -0.0451   0.4651   1.0000
   5.000   0.8501   0.03534   0.02287  -0.0435   0.4599   1.0000
   5.250   0.8709   0.03595   0.02346  -0.0426   0.4562   1.0000
   5.500   0.8901   0.03672   0.02425  -0.0415   0.4525   1.0000
   5.750   0.8874   0.03892   0.02661  -0.0390   0.4459   1.0000
   6.000   0.9045   0.03982   0.02755  -0.0378   0.4420   1.0000
   6.250   0.9305   0.04015   0.02786  -0.0374   0.4391   1.0000
   6.500   0.9073   0.04380   0.03170  -0.0337   0.4310   1.0000
   6.750   0.9224   0.04487   0.03283  -0.0325   0.4269   1.0000
   7.000   0.9492   0.04514   0.03312  -0.0321   0.4242   1.0000
   7.250   0.8932   0.05120   0.03931  -0.0273   0.4137   1.0000
   7.500   0.9159   0.05171   0.03986  -0.0266   0.4106   1.0000
   7.750   0.9468   0.05170   0.03988  -0.0263   0.4083   1.0000
   8.000   0.8762   0.06033   0.04856  -0.0241   0.3954   1.0000
   8.250   0.9035   0.06023   0.04850  -0.0231   0.3933   1.0000
   8.750   0.8810   0.06855   0.05692  -0.0231   0.3784   1.0000
   9.000   0.8465   0.07525   0.06366  -0.0238   0.3674   1.0000
   9.250   0.8704   0.07563   0.06411  -0.0230   0.3647   1.0000
   9.500   0.8426   0.08170   0.07021  -0.0239   0.3546   1.0000
   9.750   0.8628   0.08248   0.07110  -0.0232   0.3510   1.0000
  10.000   0.8474   0.08728   0.07594  -0.0239   0.3427   1.0000
  10.250   0.8596   0.08894   0.07768  -0.0236   0.3377   1.0000
  10.500   0.8854   0.08905   0.07789  -0.0227   0.3348   1.0000
  10.750   0.8608   0.09502   0.08390  -0.0240   0.3247   1.0000
  11.000   0.8828   0.09554   0.08452  -0.0232   0.3212   1.0000
  11.250   0.8660   0.10069   0.08973  -0.0244   0.3120   1.0000
  11.500   0.8837   0.10171   0.09088  -0.0239   0.3076   1.0000
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