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EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il)
Reynolds number: 500,000
Max Cl/Cd: 46.48 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ea61009-il-500000.txt
Download as CSV file: xf-ea61009-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EA 6(-1)-009 AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -1.0635   0.07234   0.06977  -0.0058   1.0000   0.0151
 -14.000  -1.1036   0.06013   0.05731  -0.0152   1.0000   0.0148
 -13.750  -1.1327   0.05221   0.04916  -0.0203   1.0000   0.0147
 -13.500  -1.1550   0.04652   0.04323  -0.0227   1.0000   0.0148
 -13.250  -1.1720   0.04222   0.03870  -0.0233   1.0000   0.0148
 -13.000  -1.1831   0.03900   0.03526  -0.0227   1.0000   0.0151
 -12.750  -1.1922   0.03629   0.03233  -0.0212   1.0000   0.0152
 -12.500  -1.1965   0.03424   0.03006  -0.0188   1.0000   0.0154
 -12.250  -1.2036   0.03127   0.02682  -0.0163   1.0000   0.0158
 -12.000  -1.1951   0.02959   0.02501  -0.0149   1.0000   0.0164
 -11.750  -1.1794   0.02865   0.02400  -0.0139   1.0000   0.0169
 -11.500  -1.1610   0.02795   0.02324  -0.0132   1.0000   0.0176
 -11.250  -1.1429   0.02702   0.02218  -0.0124   1.0000   0.0185
 -11.000  -1.1247   0.02587   0.02082  -0.0116   1.0000   0.0194
 -10.750  -1.1090   0.02422   0.01903  -0.0107   1.0000   0.0204
 -10.500  -1.0857   0.02405   0.01885  -0.0103   1.0000   0.0214
 -10.250  -1.0622   0.02381   0.01857  -0.0099   1.0000   0.0224
 -10.000  -1.0400   0.02309   0.01770  -0.0094   1.0000   0.0239
  -9.750  -1.0191   0.02196   0.01642  -0.0088   1.0000   0.0253
  -9.500  -0.9936   0.02222   0.01673  -0.0086   1.0000   0.0264
  -9.250  -0.9678   0.02256   0.01706  -0.0084   1.0000   0.0277
  -9.000  -0.9432   0.02233   0.01672  -0.0081   1.0000   0.0296
  -8.750  -0.9205   0.02135   0.01556  -0.0076   1.0000   0.0313
  -8.500  -0.8957   0.02120   0.01545  -0.0074   1.0000   0.0326
  -8.250  -0.8703   0.02123   0.01545  -0.0073   1.0000   0.0339
  -8.000  -0.8448   0.02111   0.01527  -0.0071   1.0000   0.0358
  -7.750  -0.8190   0.02107   0.01511  -0.0068   1.0000   0.0376
  -7.500  -0.7956   0.01948   0.01338  -0.0065   1.0000   0.0394
  -7.250  -0.7704   0.01896   0.01288  -0.0064   1.0000   0.0410
  -7.000  -0.7445   0.01861   0.01252  -0.0063   1.0000   0.0427
  -6.750  -0.7184   0.01817   0.01202  -0.0061   1.0000   0.0445
  -6.500  -0.6919   0.01782   0.01159  -0.0060   1.0000   0.0463
  -6.250  -0.6650   0.01776   0.01144  -0.0058   1.0000   0.0474
  -6.000  -0.6403   0.01591   0.00953  -0.0056   1.0000   0.0494
  -5.750  -0.6145   0.01497   0.00862  -0.0055   1.0000   0.0508
  -5.500  -0.5884   0.01434   0.00800  -0.0054   1.0000   0.0522
  -5.250  -0.5623   0.01382   0.00746  -0.0053   1.0000   0.0537
  -5.000  -0.5338   0.01324   0.00688  -0.0057   0.9938   0.0549
  -4.750  -0.4982   0.01266   0.00628  -0.0075   0.9785   0.0562
  -4.500  -0.4634   0.01217   0.00576  -0.0092   0.9666   0.0574
  -4.000  -0.4026   0.01160   0.00511  -0.0102   0.9424   0.0593
  -3.750  -0.3787   0.01098   0.00443  -0.0094   0.9303   0.0605
  -3.500  -0.3546   0.01052   0.00393  -0.0086   0.9198   0.0623
  -3.250  -0.3300   0.01021   0.00358  -0.0078   0.9109   0.0640
  -3.000  -0.3041   0.00994   0.00330  -0.0074   0.9022   0.0659
  -2.750  -0.2785   0.00975   0.00306  -0.0068   0.8939   0.0680
  -2.500  -0.2526   0.00957   0.00284  -0.0063   0.8843   0.0703
  -2.250  -0.2268   0.00942   0.00265  -0.0056   0.8731   0.0719
  -2.000  -0.2010   0.00926   0.00244  -0.0050   0.8616   0.0753
  -1.750  -0.1751   0.00907   0.00224  -0.0043   0.8507   0.0822
  -1.500  -0.1497   0.00847   0.00204  -0.0040   0.8411   0.1810
  -1.250  -0.1262   0.00752   0.00180  -0.0037   0.8316   0.3695
  -1.000  -0.1039   0.00663   0.00162  -0.0028   0.8182   0.5625
  -0.750  -0.0794   0.00629   0.00160  -0.0019   0.8037   0.6579
  -0.500  -0.0537   0.00617   0.00162  -0.0011   0.7892   0.7095
  -0.250  -0.0270   0.00613   0.00164  -0.0005   0.7758   0.7385
   0.000   0.0000   0.00613   0.00164   0.0000   0.7600   0.7600
   0.250   0.0270   0.00613   0.00164   0.0005   0.7386   0.7759
   0.500   0.0537   0.00617   0.00162   0.0011   0.7094   0.7892
   0.750   0.0794   0.00629   0.00160   0.0019   0.6576   0.8035
   1.000   0.1038   0.00663   0.00162   0.0028   0.5620   0.8182
   1.250   0.1262   0.00753   0.00180   0.0037   0.3690   0.8317
   1.500   0.1497   0.00847   0.00204   0.0040   0.1808   0.8411
   1.750   0.1751   0.00907   0.00224   0.0043   0.0821   0.8507
   2.000   0.2011   0.00926   0.00243   0.0050   0.0752   0.8613
   2.250   0.2268   0.00942   0.00265   0.0056   0.0719   0.8729
   2.500   0.2525   0.00957   0.00284   0.0063   0.0703   0.8843
   2.750   0.2785   0.00975   0.00306   0.0068   0.0680   0.8940
   3.000   0.3041   0.00994   0.00330   0.0074   0.0658   0.9023
   3.250   0.3300   0.01021   0.00358   0.0079   0.0640   0.9109
   3.500   0.3546   0.01052   0.00393   0.0086   0.0622   0.9198
   3.750   0.3787   0.01099   0.00445   0.0094   0.0605   0.9303
   4.000   0.4026   0.01160   0.00511   0.0102   0.0593   0.9425
   4.500   0.4635   0.01217   0.00576   0.0091   0.0574   0.9667
   4.750   0.4984   0.01266   0.00628   0.0075   0.0562   0.9786
   5.250   0.5624   0.01382   0.00747   0.0053   0.0537   1.0000
   5.500   0.5884   0.01434   0.00799   0.0054   0.0522   1.0000
   5.750   0.6146   0.01497   0.00862   0.0055   0.0508   1.0000
   6.000   0.6404   0.01589   0.00952   0.0056   0.0494   1.0000
   6.250   0.6650   0.01777   0.01145   0.0058   0.0474   1.0000
   6.500   0.6920   0.01782   0.01159   0.0059   0.0463   1.0000
   6.750   0.7185   0.01818   0.01203   0.0061   0.0446   1.0000
   7.000   0.7447   0.01862   0.01252   0.0062   0.0427   1.0000
   7.250   0.7706   0.01894   0.01285   0.0063   0.0410   1.0000
   7.500   0.7958   0.01948   0.01338   0.0064   0.0394   1.0000
   7.750   0.8193   0.02104   0.01507   0.0067   0.0376   1.0000
   8.000   0.8451   0.02110   0.01527   0.0070   0.0358   1.0000
   8.250   0.8706   0.02122   0.01544   0.0072   0.0339   1.0000
   8.500   0.8960   0.02116   0.01541   0.0074   0.0325   1.0000
   8.750   0.9207   0.02135   0.01556   0.0076   0.0313   1.0000
   9.000   0.9435   0.02235   0.01674   0.0080   0.0296   1.0000
   9.250   0.9682   0.02255   0.01705   0.0083   0.0277   1.0000
   9.500   0.9941   0.02220   0.01671   0.0085   0.0264   1.0000
   9.750   1.0197   0.02194   0.01639   0.0086   0.0253   1.0000
  10.000   1.0405   0.02309   0.01770   0.0093   0.0238   1.0000
  10.250   1.0626   0.02384   0.01861   0.0098   0.0225   1.0000
  10.500   1.0860   0.02407   0.01888   0.0102   0.0214   1.0000
  10.750   1.1093   0.02422   0.01902   0.0106   0.0204   1.0000
  11.000   1.1252   0.02581   0.02075   0.0115   0.0194   1.0000
  11.250   1.1433   0.02699   0.02215   0.0124   0.0185   1.0000
  11.500   1.1612   0.02797   0.02327   0.0131   0.0176   1.0000
  11.750   1.1795   0.02869   0.02404   0.0139   0.0169   1.0000
  12.000   1.1955   0.02958   0.02500   0.0148   0.0164   1.0000
  12.250   1.2041   0.03126   0.02681   0.0162   0.0159   1.0000
  12.500   1.1975   0.03420   0.03002   0.0187   0.0154   1.0000
  12.750   1.1927   0.03630   0.03235   0.0211   0.0152   1.0000
  13.000   1.1835   0.03902   0.03529   0.0226   0.0150   1.0000
  13.250   1.1710   0.04239   0.03889   0.0232   0.0149   1.0000
  13.500   1.1541   0.04672   0.04344   0.0226   0.0148   1.0000
  13.750   1.1331   0.05224   0.04919   0.0202   0.0148   1.0000
  14.000   1.1040   0.06017   0.05736   0.0151   0.0148   1.0000
  14.250   1.0590   0.07346   0.07090   0.0048   0.0151   1.0000
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