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EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 434 AIRFOIL (e434-il)
Reynolds number: 50,000
Max Cl/Cd: 8.58 at α=13.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e434-il-50000.txt
Download as CSV file: xf-e434-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 434 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.4565   0.11558   0.11047  -0.0152   1.0000   0.2166
  -7.000  -0.4363   0.11124   0.10613  -0.0128   1.0000   0.2256
  -6.750  -0.4657   0.11068   0.10568  -0.0106   1.0000   0.2312
  -6.500  -0.5060   0.11032   0.10544  -0.0097   1.0000   0.2329
  -6.250  -0.4852   0.10640   0.10154  -0.0058   1.0000   0.2451
  -6.000  -0.5296   0.10559   0.10082  -0.0076   1.0000   0.2492
  -5.750  -0.5144   0.10206   0.09733  -0.0031   1.0000   0.2627
  -5.500  -0.5156   0.09922   0.09455  -0.0006   1.0000   0.2733
  -5.250  -0.5271   0.09661   0.09200   0.0008   1.0000   0.2864
  -5.000  -0.5366   0.09413   0.08956   0.0020   1.0000   0.3010
  -4.750  -0.5371   0.09155   0.08703   0.0051   1.0000   0.3195
  -4.250  -0.5443   0.08668   0.08225   0.0111   1.0000   0.3671
  -2.750  -0.3942   0.05401   0.04653  -0.0306   1.0000   0.1357
  -2.500  -0.3659   0.05074   0.04260  -0.0313   1.0000   0.1207
  -2.250  -0.3430   0.04820   0.03974  -0.0314   1.0000   0.1158
  -2.000  -0.3134   0.04625   0.03682  -0.0313   1.0000   0.1072
  -1.750  -0.2903   0.04428   0.03457  -0.0311   1.0000   0.1058
  -1.500  -0.2666   0.04292   0.03281  -0.0306   1.0000   0.1062
  -1.250  -0.2440   0.04157   0.03131  -0.0303   1.0000   0.1117
  -1.000  -0.2214   0.04077   0.03030  -0.0297   1.0000   0.1174
  -0.750  -0.1986   0.04000   0.02934  -0.0288   1.0000   0.1266
  -0.500  -0.1770   0.03952   0.02881  -0.0277   1.0000   0.1429
  -0.250  -0.1529   0.03900   0.02837  -0.0269   1.0000   0.1806
   0.000  -0.1351   0.03487   0.02788  -0.0218   1.0000   1.0000
   0.250  -0.1149   0.03560   0.02768  -0.0211   1.0000   1.0000
   0.500  -0.0964   0.03636   0.02799  -0.0208   1.0000   1.0000
   0.750  -0.0782   0.03716   0.02842  -0.0207   1.0000   1.0000
   1.000  -0.0601   0.03802   0.02897  -0.0206   1.0000   1.0000
   1.250  -0.0422   0.03892   0.02960  -0.0205   1.0000   1.0000
   1.500  -0.0244   0.03988   0.03031  -0.0206   1.0000   1.0000
   1.750  -0.0067   0.04087   0.03108  -0.0206   1.0000   1.0000
   2.000   0.0107   0.04192   0.03193  -0.0207   1.0000   1.0000
   2.250   0.0280   0.04301   0.03284  -0.0208   1.0000   1.0000
   2.500   0.0451   0.04415   0.03383  -0.0210   1.0000   1.0000
   2.750   0.0620   0.04534   0.03487  -0.0212   1.0000   1.0000
   3.000   0.0933   0.04766   0.03701  -0.0242   0.9944   1.0000
   3.250   0.1291   0.05031   0.03950  -0.0280   0.9841   1.0000
   3.500   0.1632   0.05283   0.04188  -0.0316   0.9718   1.0000
   3.750   0.1941   0.05505   0.04401  -0.0346   0.9585   1.0000
   4.000   0.2242   0.05726   0.04615  -0.0374   0.9442   1.0000
   4.250   0.2508   0.05917   0.04800  -0.0395   0.9297   1.0000
   4.500   0.2778   0.06122   0.05000  -0.0416   0.9143   1.0000
   4.750   0.3020   0.06308   0.05183  -0.0431   0.8992   1.0000
   5.000   0.3266   0.06504   0.05377  -0.0447   0.8837   1.0000
   5.250   0.3493   0.06694   0.05567  -0.0460   0.8685   1.0000
   5.500   0.3736   0.06901   0.05774  -0.0474   0.8525   1.0000
   5.750   0.3956   0.07097   0.05972  -0.0485   0.8371   1.0000
   6.000   0.4198   0.07313   0.06189  -0.0499   0.8209   1.0000
   6.250   0.4431   0.07528   0.06407  -0.0511   0.8048   1.0000
   6.500   0.4719   0.07782   0.06664  -0.0529   0.7879   1.0000
   6.750   0.4899   0.07969   0.06856  -0.0533   0.7720   1.0000
   7.000   0.5038   0.08135   0.07029  -0.0532   0.7553   1.0000
   7.250   0.5168   0.08292   0.07191  -0.0530   0.7367   1.0000
   7.500   0.6196   0.07888   0.06789  -0.0538   0.6390   1.0000
   7.750   0.6428   0.08020   0.06933  -0.0539   0.6231   1.0000
   8.000   0.6646   0.08154   0.07077  -0.0540   0.6077   1.0000
   8.250   0.6854   0.08292   0.07225  -0.0539   0.5925   1.0000
   8.500   0.7048   0.08435   0.07378  -0.0538   0.5776   1.0000
   8.750   0.7242   0.08575   0.07532  -0.0536   0.5626   1.0000
   9.000   0.7406   0.08736   0.07704  -0.0533   0.5481   1.0000
   9.250   0.7585   0.08883   0.07863  -0.0530   0.5332   1.0000
   9.500   0.7734   0.09056   0.08050  -0.0527   0.5188   1.0000
   9.750   0.7898   0.09214   0.08221  -0.0523   0.5040   1.0000
  10.000   0.8034   0.09400   0.08420  -0.0520   0.4898   1.0000
  10.250   0.8196   0.09555   0.08589  -0.0515   0.4747   1.0000
  10.500   0.8318   0.09757   0.08807  -0.0512   0.4606   1.0000
  10.750   0.8456   0.09937   0.09000  -0.0507   0.4459   1.0000
  11.000   0.8574   0.10145   0.09223  -0.0504   0.4317   1.0000
  11.250   0.8702   0.10335   0.09427  -0.0499   0.4171   1.0000
  11.500   0.8817   0.10553   0.09661  -0.0495   0.4033   1.0000
  11.750   0.8940   0.10754   0.09877  -0.0491   0.3891   1.0000
  12.000   0.9066   0.10951   0.10089  -0.0486   0.3750   1.0000
  12.250   0.9200   0.11132   0.10286  -0.0480   0.3608   1.0000
  12.500   0.9349   0.11291   0.10461  -0.0473   0.3467   1.0000
  12.750   0.9496   0.11437   0.10626  -0.0465   0.3323   1.0000
  13.000   0.9667   0.11538   0.10746  -0.0454   0.3180   1.0000
  13.250   0.9192   0.12728   0.11924  -0.0500   0.3125   1.0000
  13.500   1.0017   0.11672   0.10920  -0.0428   0.2890   1.0000
  13.750   0.9433   0.13179   0.12404  -0.0493   0.2870   1.0000
  14.000   0.9167   0.14075   0.13296  -0.0531   0.2828   1.0000
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