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EPPLER 334 AIRFOIL (e334-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 334 AIRFOIL (e334-il)
Reynolds number: 50,000
Max Cl/Cd: 27.92 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e334-il-50000-n5.txt
Download as CSV file: xf-e334-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3104   0.10185   0.09555  -0.0286   1.0000   0.1035
  -8.250  -0.3281   0.10029   0.09416  -0.0321   1.0000   0.1062
  -7.750  -0.3367   0.09389   0.08803  -0.0329   1.0000   0.1086
  -7.500  -0.3229   0.09014   0.08435  -0.0310   1.0000   0.1116
  -7.250  -0.3262   0.08761   0.08193  -0.0301   1.0000   0.1142
  -7.000  -0.3333   0.08517   0.07962  -0.0298   1.0000   0.1173
  -6.750  -0.3633   0.08489   0.07945  -0.0307   1.0000   0.1226
  -5.500  -0.2523   0.05929   0.05288  -0.0494   0.9146   0.0515
  -5.250  -0.2252   0.05513   0.04857  -0.0519   0.8965   0.0486
  -4.750  -0.1708   0.04764   0.03994  -0.0547   0.8602   0.0429
  -4.500  -0.1450   0.04473   0.03659  -0.0551   0.8427   0.0430
  -3.750  -0.0711   0.03754   0.02811  -0.0538   0.7930   0.0429
  -3.500  -0.0464   0.03550   0.02568  -0.0529   0.7775   0.0427
  -3.250  -0.0209   0.03365   0.02340  -0.0520   0.7628   0.0426
  -3.000   0.0059   0.03196   0.02128  -0.0510   0.7488   0.0429
  -2.750   0.0328   0.03037   0.01946  -0.0505   0.7357   0.0444
  -2.500   0.0608   0.02917   0.01802  -0.0500   0.7230   0.0476
  -2.250   0.0903   0.02804   0.01654  -0.0493   0.7096   0.0513
  -2.000   0.1234   0.02684   0.01514  -0.0494   0.6972   0.0544
  -1.750   0.1548   0.02600   0.01406  -0.0492   0.6858   0.0625
  -1.500   0.1822   0.02517   0.01311  -0.0486   0.6749   0.0709
  -1.250   0.3325   0.02063   0.01114  -0.0683   0.6603   1.0000
  -1.000   0.3545   0.02078   0.01088  -0.0672   0.6492   1.0000
  -0.750   0.3769   0.02092   0.01063  -0.0661   0.6397   1.0000
  -0.500   0.3986   0.02112   0.01057  -0.0650   0.6291   1.0000
  -0.250   0.4212   0.02134   0.01051  -0.0642   0.6199   1.0000
   0.000   0.4437   0.02154   0.01047  -0.0632   0.6109   1.0000
   0.250   0.4654   0.02182   0.01056  -0.0623   0.6018   1.0000
   0.500   0.4880   0.02205   0.01057  -0.0613   0.5939   1.0000
   0.750   0.5091   0.02238   0.01077  -0.0603   0.5853   1.0000
   1.000   0.5314   0.02264   0.01085  -0.0593   0.5780   1.0000
   1.250   0.5520   0.02302   0.01113  -0.0583   0.5699   1.0000
   1.500   0.5737   0.02333   0.01131  -0.0572   0.5629   1.0000
   1.750   0.5944   0.02373   0.01162  -0.0561   0.5557   1.0000
   2.000   0.6149   0.02412   0.01193  -0.0550   0.5485   1.0000
   2.250   0.6367   0.02446   0.01215  -0.0539   0.5425   1.0000
   2.500   0.6551   0.02500   0.01270  -0.0526   0.5349   1.0000
   2.750   0.6770   0.02533   0.01293  -0.0515   0.5294   1.0000
   3.000   0.6948   0.02592   0.01354  -0.0502   0.5223   1.0000
   3.250   0.7145   0.02639   0.01398  -0.0489   0.5161   1.0000
   3.500   0.7362   0.02677   0.01428  -0.0478   0.5111   1.0000
   3.750   0.7512   0.02752   0.01511  -0.0462   0.5037   1.0000
   4.000   0.7721   0.02793   0.01548  -0.0450   0.4983   1.0000
   4.250   0.7892   0.02859   0.01620  -0.0435   0.4924   1.0000
   4.500   0.8052   0.02929   0.01695  -0.0419   0.4860   1.0000
   4.750   0.8274   0.02964   0.01726  -0.0408   0.4812   1.0000
   5.000   0.8393   0.03061   0.01834  -0.0389   0.4746   1.0000
   5.250   0.8563   0.03127   0.01903  -0.0373   0.4688   1.0000
   5.500   0.8804   0.03155   0.01931  -0.0365   0.4645   1.0000
   5.750   0.8857   0.03288   0.02082  -0.0339   0.4569   1.0000
   6.000   0.9048   0.03345   0.02143  -0.0327   0.4517   1.0000
   6.250   0.9224   0.03413   0.02214  -0.0313   0.4465   1.0000
   6.500   0.9293   0.03543   0.02363  -0.0290   0.4393   1.0000
   6.750   0.9524   0.03579   0.02403  -0.0281   0.4347   1.0000
   7.000   0.9572   0.03727   0.02566  -0.0258   0.4277   1.0000
   7.250   0.9710   0.03821   0.02668  -0.0242   0.4215   1.0000
   7.500   1.0006   0.03820   0.02673  -0.0239   0.4175   1.0000
   7.750   0.9877   0.04079   0.02954  -0.0204   0.4086   1.0000
   8.000   1.0129   0.04101   0.02982  -0.0197   0.4037   1.0000
   8.250   1.0034   0.04347   0.03244  -0.0168   0.3957   1.0000
   8.500   1.0192   0.04424   0.03331  -0.0155   0.3896   1.0000
   8.750   1.0232   0.04585   0.03505  -0.0136   0.3832   1.0000
   9.000   1.0097   0.04849   0.03780  -0.0107   0.3751   1.0000
   9.250   1.0582   0.04709   0.03652  -0.0113   0.3713   1.0000
   9.500   0.9855   0.05445   0.04389  -0.0069   0.3593   1.0000
   9.750   1.0063   0.05476   0.04432  -0.0059   0.3542   1.0000
  10.000   0.9723   0.06077   0.05037  -0.0058   0.3428   1.0000
  10.500   0.9694   0.06663   0.05641  -0.0055   0.3267   1.0000
  11.000   0.9696   0.07241   0.06238  -0.0055   0.3107   1.0000
  11.500   0.9201   0.08546   0.07549  -0.0089   0.2870   1.0000
  11.750   0.9476   0.08458   0.07478  -0.0074   0.2830   1.0000
  12.000   0.9248   0.09109   0.08131  -0.0093   0.2716   1.0000
  12.250   0.9551   0.08965   0.08005  -0.0077   0.2681   1.0000
  12.500   0.9314   0.09649   0.08692  -0.0099   0.2564   1.0000
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