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EPPLER 334 AIRFOIL (e334-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 334 AIRFOIL (e334-il)
Reynolds number: 50,000
Max Cl/Cd: 16.57 at α=0.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e334-il-50000.txt
Download as CSV file: xf-e334-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 334 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  -0.3270   0.10291   0.09688  -0.0247   1.0000   0.1886
  -8.000  -0.3059   0.09805   0.09205  -0.0227   1.0000   0.1982
  -7.750  -0.3279   0.09711   0.09130  -0.0241   1.0000   0.2051
  -7.500  -0.3095   0.09279   0.08704  -0.0221   1.0000   0.2170
  -7.250  -0.3405   0.09216   0.08666  -0.0224   1.0000   0.2218
  -7.000  -0.3282   0.08846   0.08305  -0.0202   1.0000   0.2363
  -6.750  -0.3267   0.08562   0.08036  -0.0181   1.0000   0.2482
  -6.500  -0.3600   0.08520   0.08019  -0.0170   1.0000   0.2548
  -6.250  -0.3583   0.08259   0.07776  -0.0131   1.0000   0.2690
  -6.000  -0.3937   0.08289   0.07826  -0.0087   1.0000   0.2703
  -5.750  -0.4282   0.08323   0.07874  -0.0047   1.0000   0.2711
  -5.500  -0.4340   0.08139   0.07705  -0.0001   1.0000   0.2806
  -5.250  -0.4557   0.08037   0.07611   0.0015   0.9985   0.2920
  -5.000   0.0074   0.05730   0.05216  -0.0084   1.0000   0.9203
  -4.000  -0.0857   0.05803   0.05368  -0.0011   0.9604   0.7887
  -3.750  -0.1425   0.05708   0.05284  -0.0030   0.9329   0.6992
  -3.500  -0.1894   0.05470   0.05053  -0.0054   0.9065   0.6374
  -3.250  -0.1701   0.04747   0.04132  -0.0486   0.8772   0.3054
  -3.000  -0.0922   0.04298   0.03534  -0.0564   0.8670   0.1666
  -2.750  -0.0443   0.04040   0.03195  -0.0581   0.8556   0.1350
  -2.500  -0.0096   0.03887   0.02977  -0.0581   0.8421   0.1212
  -2.250   0.0256   0.03692   0.02749  -0.0586   0.8299   0.1177
  -2.000   0.0743   0.03493   0.02506  -0.0606   0.8205   0.1186
  -1.750   0.1062   0.03385   0.02367  -0.0603   0.8076   0.1201
  -1.500   0.3466   0.02450   0.01671  -0.0894   0.8024   1.0000
  -1.250   0.3705   0.02487   0.01650  -0.0883   0.7891   1.0000
  -1.000   0.3879   0.02549   0.01679  -0.0868   0.7754   1.0000
  -0.750   0.4049   0.02616   0.01719  -0.0852   0.7627   1.0000
  -0.500   0.4247   0.02674   0.01750  -0.0839   0.7517   1.0000
  -0.250   0.4449   0.02730   0.01781  -0.0827   0.7411   1.0000
   0.000   0.4570   0.02828   0.01864  -0.0808   0.7296   1.0000
   0.250   0.4781   0.02886   0.01901  -0.0796   0.7208   1.0000
   0.500   0.4900   0.02990   0.01993  -0.0777   0.7104   1.0000
   0.750   0.5030   0.03094   0.02085  -0.0759   0.7013   1.0000
   1.000   0.5201   0.03175   0.02152  -0.0744   0.6926   1.0000
   1.250   0.5257   0.03322   0.02293  -0.0720   0.6838   1.0000
   1.500   0.5443   0.03401   0.02360  -0.0706   0.6760   1.0000
   1.750   0.5433   0.03583   0.02537  -0.0677   0.6675   1.0000
   2.000   0.5577   0.03689   0.02635  -0.0661   0.6602   1.0000
   2.250   0.5559   0.03879   0.02820  -0.0631   0.6527   1.0000
   2.500   0.5577   0.04048   0.02984  -0.0604   0.6453   1.0000
   2.750   0.5709   0.04175   0.03103  -0.0588   0.6391   1.0000
   3.000   0.5397   0.04495   0.03424  -0.0536   0.6322   1.0000
   3.250   0.5697   0.04558   0.03478  -0.0535   0.6260   1.0000
   3.500   0.5351   0.04897   0.03813  -0.0482   0.6210   1.0000
   3.750   0.5080   0.05191   0.04102  -0.0438   0.6171   1.0000
   4.000   0.5192   0.05358   0.04263  -0.0427   0.6117   1.0000
   4.250   0.5307   0.05542   0.04442  -0.0418   0.6069   1.0000
   4.500   0.5135   0.05838   0.04735  -0.0394   0.6051   1.0000
   4.750   0.5062   0.06106   0.05000  -0.0380   0.6037   1.0000
   5.000   0.5039   0.06370   0.05262  -0.0371   0.6037   1.0000
   5.250   0.5068   0.06639   0.05531  -0.0368   0.6056   1.0000
   5.500   0.5153   0.06920   0.05812  -0.0372   0.6092   1.0000
   5.750   0.4105   0.07692   0.06598  -0.0377   0.7385   1.0000
   6.000   0.4248   0.07863   0.06767  -0.0374   0.7241   1.0000
   6.250   0.4311   0.08005   0.06908  -0.0363   0.7104   1.0000
   6.500   0.4409   0.08200   0.07101  -0.0357   0.6987   1.0000
   6.750   0.4693   0.08529   0.07430  -0.0373   0.6890   1.0000
   7.000   0.4842   0.08727   0.07628  -0.0371   0.6749   1.0000
   7.250   0.4865   0.08870   0.07771  -0.0359   0.6619   1.0000
   7.500   0.4963   0.09085   0.07987  -0.0355   0.6500   1.0000
   7.750   0.5293   0.09474   0.08378  -0.0374   0.6406   1.0000
   8.000   0.5328   0.09612   0.08521  -0.0363   0.6268   1.0000
   8.250   0.5349   0.09792   0.08702  -0.0354   0.6145   1.0000
   8.500   0.5480   0.10062   0.08975  -0.0356   0.6043   1.0000
   8.750   0.5774   0.10422   0.09340  -0.0369   0.5929   1.0000
   9.000   0.5715   0.10542   0.09463  -0.0355   0.5805   1.0000
   9.250   0.5787   0.10791   0.09716  -0.0354   0.5699   1.0000
   9.500   0.6162   0.11263   0.10198  -0.0372   0.5600   1.0000
   9.750   0.6049   0.11331   0.10270  -0.0357   0.5475   1.0000
  10.000   0.6085   0.11577   0.10519  -0.0355   0.5368   1.0000
  10.250   0.6426   0.12049   0.11001  -0.0371   0.5276   1.0000
  10.500   0.6345   0.12151   0.11107  -0.0361   0.5151   1.0000
  10.750   0.6364   0.12407   0.11367  -0.0361   0.5055   1.0000
  11.000   0.6693   0.12894   0.11868  -0.0374   0.4957   1.0000
  11.250   0.6585   0.12985   0.11963  -0.0367   0.4841   1.0000
  11.500   0.6637   0.13288   0.12273  -0.0371   0.4757   1.0000
  11.750   0.6944   0.13755   0.12753  -0.0380   0.4647   1.0000
  12.000   0.6796   0.13846   0.12845  -0.0377   0.4543   1.0000
  12.250   0.6959   0.14260   0.13268  -0.0385   0.4470   1.0000
  12.500   0.7065   0.14533   0.13551  -0.0388   0.4346   1.0000
  12.750   0.7011   0.14753   0.13777  -0.0393   0.4261   1.0000
  13.000   0.7363   0.15361   0.14401  -0.0402   0.4173   1.0000
  13.250   0.7176   0.15368   0.14409  -0.0405   0.4071   1.0000
  13.500   0.7315   0.15786   0.14836  -0.0413   0.4000   1.0000
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