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EPPLER 426 AIRFOIL (e426-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 426 AIRFOIL (e426-il)
Reynolds number: 50,000
Max Cl/Cd: 22.85 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e426-il-50000.txt
Download as CSV file: xf-e426-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 426 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4738   0.09579   0.08792   0.0240   1.0000   0.4383
  -8.000  -0.4642   0.09286   0.08497   0.0245   1.0000   0.4553
  -7.500  -0.6187   0.06977   0.06233  -0.0053   1.0000   0.2828
  -7.250  -0.6143   0.06463   0.05711  -0.0073   1.0000   0.2804
  -7.000  -0.6133   0.05904   0.05142  -0.0099   1.0000   0.2771
  -6.750  -0.6156   0.05297   0.04514  -0.0132   1.0000   0.2754
  -6.500  -0.6108   0.04787   0.03974  -0.0155   1.0000   0.2761
  -6.250  -0.6004   0.04345   0.03496  -0.0170   1.0000   0.2769
  -6.000  -0.5872   0.03967   0.03072  -0.0181   1.0000   0.2805
  -5.750  -0.5680   0.03722   0.02810  -0.0179   1.0000   0.2855
  -5.500  -0.5471   0.03512   0.02582  -0.0176   1.0000   0.2905
  -5.250  -0.5266   0.03276   0.02310  -0.0177   1.0000   0.2956
  -5.000  -0.5048   0.03091   0.02108  -0.0173   1.0000   0.3025
  -4.750  -0.4823   0.02946   0.01950  -0.0167   1.0000   0.3118
  -4.500  -0.4595   0.02799   0.01793  -0.0161   1.0000   0.3208
  -4.250  -0.4362   0.02658   0.01629  -0.0157   1.0000   0.3311
  -4.000  -0.4131   0.02547   0.01526  -0.0148   1.0000   0.3422
  -3.750  -0.3903   0.02446   0.01425  -0.0139   1.0000   0.3564
  -3.500  -0.3675   0.02353   0.01336  -0.0130   1.0000   0.3721
  -3.250  -0.3450   0.02271   0.01259  -0.0120   1.0000   0.3899
  -3.000  -0.3229   0.02196   0.01191  -0.0110   1.0000   0.4108
  -2.750  -0.3013   0.02128   0.01137  -0.0098   1.0000   0.4351
  -2.500  -0.2805   0.02066   0.01091  -0.0085   1.0000   0.4639
  -2.250  -0.2611   0.02007   0.01053  -0.0068   1.0000   0.4987
  -2.000  -0.2435   0.01953   0.01033  -0.0047   1.0000   0.5426
  -1.750  -0.2284   0.01901   0.01021  -0.0018   1.0000   0.6057
  -1.500  -0.2187   0.01864   0.01026   0.0026   1.0000   0.6834
  -1.250  -0.2130   0.01837   0.01034   0.0081   1.0000   0.7605
  -1.000  -0.2058   0.01820   0.01042   0.0133   1.0000   0.8386
  -0.750  -0.1419   0.01840   0.01069   0.0089   1.0000   0.9401
  -0.500  -0.0396   0.01843   0.01049  -0.0061   1.0000   1.0000
  -0.250  -0.0714   0.01825   0.01022  -0.0010   1.0000   1.0000
   0.000  -0.0689   0.01849   0.01028   0.0001   1.0000   1.0000
   0.250  -0.0142   0.01926   0.01091  -0.0072   0.9832   1.0000
   0.500   0.0780   0.01981   0.01142  -0.0197   0.9467   1.0000
   0.750   0.1821   0.01973   0.01139  -0.0327   0.9123   1.0000
   1.000   0.2548   0.01942   0.01112  -0.0391   0.8733   1.0000
   1.250   0.3034   0.01919   0.01085  -0.0408   0.8315   1.0000
   1.500   0.3294   0.01923   0.01077  -0.0386   0.7873   1.0000
   1.750   0.3515   0.01931   0.01067  -0.0354   0.7431   1.0000
   2.000   0.3703   0.01953   0.01069  -0.0319   0.6954   1.0000
   2.250   0.3899   0.01989   0.01079  -0.0288   0.6459   1.0000
   2.500   0.4104   0.02036   0.01100  -0.0263   0.5992   1.0000
   2.750   0.4325   0.02089   0.01124  -0.0242   0.5602   1.0000
   3.000   0.4556   0.02155   0.01171  -0.0228   0.5273   1.0000
   3.250   0.4791   0.02228   0.01230  -0.0216   0.4995   1.0000
   3.500   0.5033   0.02298   0.01283  -0.0205   0.4764   1.0000
   3.750   0.5280   0.02374   0.01344  -0.0195   0.4569   1.0000
   4.000   0.5521   0.02461   0.01429  -0.0187   0.4379   1.0000
   4.250   0.5763   0.02549   0.01513  -0.0179   0.4207   1.0000
   4.500   0.6009   0.02641   0.01601  -0.0172   0.4055   1.0000
   4.750   0.6253   0.02737   0.01694  -0.0164   0.3909   1.0000
   5.000   0.6486   0.02855   0.01823  -0.0158   0.3769   1.0000
   5.250   0.6716   0.02982   0.01963  -0.0152   0.3637   1.0000
   5.500   0.6946   0.03122   0.02111  -0.0146   0.3524   1.0000
   5.750   0.7196   0.03236   0.02215  -0.0138   0.3413   1.0000
   6.000   0.7390   0.03420   0.02431  -0.0133   0.3295   1.0000
   6.250   0.7594   0.03614   0.02641  -0.0127   0.3203   1.0000
   6.500   0.7819   0.03769   0.02801  -0.0120   0.3104   1.0000
   6.750   0.7957   0.04049   0.03118  -0.0117   0.3013   1.0000
   7.000   0.8200   0.04200   0.03264  -0.0108   0.2931   1.0000
   7.250   0.8243   0.04614   0.03729  -0.0109   0.2860   1.0000
   7.500   0.8458   0.04786   0.03902  -0.0100   0.2775   1.0000
   7.750   0.8450   0.05280   0.04435  -0.0104   0.2730   1.0000
   8.000   0.8280   0.05965   0.05155  -0.0122   0.2706   1.0000
   8.250   0.7995   0.06792   0.06000  -0.0155   0.2714   1.0000
   8.500   0.7756   0.07582   0.06794  -0.0192   0.2738   1.0000
   8.750   0.7693   0.08193   0.07405  -0.0214   0.2756   1.0000
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