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EPPLER 339 AIRFOIL (e339-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 339 AIRFOIL (e339-il)
Reynolds number: 50,000
Max Cl/Cd: 26.09 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e339-il-50000-n5.txt
Download as CSV file: xf-e339-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2839   0.10268   0.09651  -0.0336   1.0000   0.1109
  -8.500  -0.3059   0.10102   0.09504  -0.0368   1.0000   0.1148
  -8.250  -0.3356   0.09965   0.09386  -0.0385   1.0000   0.1156
  -8.000  -0.3260   0.09514   0.08949  -0.0373   1.0000   0.1172
  -7.750  -0.3113   0.09158   0.08602  -0.0353   1.0000   0.1198
  -7.500  -0.3194   0.08931   0.08392  -0.0337   1.0000   0.1217
  -7.250  -0.3330   0.08750   0.08229  -0.0321   0.9971   0.1234
  -7.000  -0.3378   0.08369   0.07835  -0.0423   0.9511   0.1332
  -6.500  -0.2793   0.06886   0.06303  -0.0523   0.9124   0.0608
  -6.250  -0.2585   0.06370   0.05757  -0.0558   0.8924   0.0520
  -6.000  -0.2397   0.05889   0.05232  -0.0581   0.8730   0.0467
  -5.750  -0.2181   0.05527   0.04843  -0.0594   0.8543   0.0455
  -5.500  -0.1988   0.05194   0.04473  -0.0599   0.8359   0.0446
  -5.250  -0.1802   0.04904   0.04144  -0.0596   0.8181   0.0445
  -5.000  -0.1622   0.04639   0.03839  -0.0587   0.8012   0.0445
  -4.750  -0.1438   0.04397   0.03554  -0.0575   0.7851   0.0449
  -4.500  -0.1244   0.04172   0.03286  -0.0562   0.7701   0.0448
  -4.250  -0.1033   0.03951   0.03018  -0.0549   0.7565   0.0447
  -4.000  -0.0817   0.03752   0.02775  -0.0535   0.7427   0.0444
  -3.750  -0.0591   0.03572   0.02554  -0.0522   0.7292   0.0443
  -3.500  -0.0338   0.03397   0.02334  -0.0510   0.7170   0.0447
  -3.250  -0.0064   0.03239   0.02132  -0.0502   0.7056   0.0459
  -3.000   0.0204   0.03109   0.01970  -0.0494   0.6931   0.0486
  -2.750   0.0497   0.02997   0.01838  -0.0492   0.6824   0.0521
  -2.500   0.0848   0.02878   0.01685  -0.0494   0.6715   0.0553
  -2.250   0.1190   0.02785   0.01581  -0.0500   0.6605   0.0620
  -2.000   0.1506   0.02698   0.01477  -0.0501   0.6514   0.0707
  -1.500   0.3703   0.02273   0.01272  -0.0755   0.6264   1.0000
  -1.250   0.3925   0.02284   0.01249  -0.0747   0.6177   1.0000
  -1.000   0.4143   0.02300   0.01237  -0.0738   0.6092   1.0000
  -0.750   0.4362   0.02316   0.01227  -0.0729   0.6009   1.0000
  -0.500   0.4580   0.02334   0.01222  -0.0721   0.5935   1.0000
  -0.250   0.4791   0.02358   0.01228  -0.0711   0.5855   1.0000
   0.000   0.5018   0.02375   0.01220  -0.0702   0.5795   1.0000
   0.250   0.5215   0.02409   0.01246  -0.0692   0.5714   1.0000
   0.500   0.5430   0.02434   0.01253  -0.0682   0.5650   1.0000
   0.750   0.5641   0.02464   0.01268  -0.0672   0.5589   1.0000
   1.000   0.5834   0.02505   0.01303  -0.0660   0.5519   1.0000
   1.250   0.6049   0.02534   0.01317  -0.0650   0.5465   1.0000
   1.500   0.6246   0.02576   0.01351  -0.0639   0.5407   1.0000
   1.750   0.6429   0.02624   0.01396  -0.0626   0.5342   1.0000
   2.000   0.6640   0.02658   0.01419  -0.0615   0.5292   1.0000
   2.250   0.6832   0.02705   0.01460  -0.0602   0.5240   1.0000
   2.500   0.6994   0.02768   0.01526  -0.0587   0.5178   1.0000
   2.750   0.7192   0.02810   0.01562  -0.0575   0.5129   1.0000
   3.000   0.7409   0.02844   0.01586  -0.0564   0.5089   1.0000
   3.250   0.7524   0.02935   0.01689  -0.0544   0.5024   1.0000
   3.500   0.7695   0.02993   0.01746  -0.0529   0.4974   1.0000
   3.750   0.7905   0.03030   0.01776  -0.0517   0.4935   1.0000
   4.000   0.8024   0.03120   0.01872  -0.0497   0.4881   1.0000
   4.250   0.8137   0.03208   0.01967  -0.0475   0.4825   1.0000
   4.500   0.8317   0.03260   0.02021  -0.0460   0.4783   1.0000
   4.750   0.8545   0.03291   0.02045  -0.0451   0.4750   1.0000
   5.000   0.8517   0.03451   0.02224  -0.0414   0.4683   1.0000
   5.250   0.8630   0.03535   0.02312  -0.0392   0.4634   1.0000
   5.500   0.8830   0.03576   0.02352  -0.0379   0.4597   1.0000
   5.750   0.8865   0.03703   0.02491  -0.0349   0.4547   1.0000
   6.000   0.8813   0.03866   0.02666  -0.0310   0.4487   1.0000
   6.250   0.8960   0.03929   0.02730  -0.0291   0.4444   1.0000
   6.500   0.9212   0.03947   0.02747  -0.0284   0.4414   1.0000
   6.750   0.8796   0.04290   0.03108  -0.0211   0.4332   1.0000
   7.000   0.8869   0.04392   0.03213  -0.0187   0.4285   1.0000
   7.250   0.9143   0.04396   0.03218  -0.0182   0.4254   1.0000
   7.500   0.8353   0.04979   0.03808  -0.0092   0.4146   1.0000
   7.750   0.8546   0.05029   0.03861  -0.0081   0.4108   1.0000
   8.000   0.8905   0.04981   0.03821  -0.0081   0.4083   1.0000
   8.500   0.7779   0.06423   0.05265  -0.0042   0.3832   1.0000
   8.750   0.7917   0.06543   0.05393  -0.0034   0.3784   1.0000
   9.000   0.8185   0.06528   0.05384  -0.0025   0.3759   1.0000
   9.500   0.8056   0.07217   0.06082  -0.0021   0.3604   1.0000
  10.000   0.7981   0.07866   0.06742  -0.0021   0.3456   1.0000
  10.500   0.7953   0.08484   0.07373  -0.0023   0.3314   1.0000
  10.750   0.8211   0.08477   0.07376  -0.0014   0.3282   1.0000
  11.000   0.7968   0.09063   0.07966  -0.0026   0.3174   1.0000
  11.250   0.8185   0.09108   0.08020  -0.0019   0.3137   1.0000
  11.500   0.8015   0.09620   0.08537  -0.0030   0.3039   1.0000
  11.750   0.8196   0.09706   0.08636  -0.0026   0.2994   1.0000
  12.000   0.8088   0.10161   0.09096  -0.0036   0.2909   1.0000
  12.250   0.8228   0.10294   0.09240  -0.0034   0.2854   1.0000
  12.750   0.8260   0.10899   0.09862  -0.0045   0.2717   1.0000
  13.000   0.8523   0.10857   0.09833  -0.0035   0.2683   1.0000
  13.250   0.8309   0.11493   0.10475  -0.0057   0.2581   1.0000
  13.500   0.8544   0.11485   0.10480  -0.0049   0.2545   1.0000
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