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EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)
Reynolds number: 100,000
Max Cl/Cd: 51.34 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ste87391-il-100000.txt
Download as CSV file: xf-ste87391-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STE 87(-3)-914 AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.6712   0.06653   0.06201  -0.0480   1.0019   0.0759
  -7.250  -0.6777   0.04814   0.04139  -0.0580   1.0019   0.0610
  -7.000  -0.6574   0.04480   0.03779  -0.0584   1.0019   0.0602
  -6.750  -0.6341   0.04155   0.03405  -0.0593   1.0019   0.0596
  -6.500  -0.6092   0.03892   0.03093  -0.0599   1.0019   0.0594
  -6.250  -0.5835   0.03686   0.02843  -0.0603   1.0019   0.0601
  -6.000  -0.5590   0.03531   0.02668  -0.0605   1.0019   0.0624
  -5.750  -0.5347   0.03413   0.02538  -0.0604   1.0019   0.0649
  -5.500  -0.5091   0.03300   0.02397  -0.0602   1.0019   0.0666
  -5.250  -0.4846   0.03194   0.02298  -0.0601   1.0019   0.0688
  -5.000  -0.4591   0.03116   0.02217  -0.0601   1.0019   0.0720
  -4.750  -0.4326   0.03042   0.02151  -0.0605   1.0019   0.0770
  -4.500  -0.4046   0.02982   0.02095  -0.0614   1.0019   0.0859
  -4.250  -0.3732   0.02913   0.02040  -0.0629   1.0019   0.1027
  -4.000  -0.3377   0.02860   0.02062  -0.0657   1.0019   0.2321
  -3.750  -0.3138   0.02903   0.02099  -0.0660   1.0019   0.2713
  -3.500  -0.2900   0.02936   0.02124  -0.0662   1.0019   0.2959
  -3.250  -0.2664   0.02974   0.02167  -0.0666   1.0019   0.3270
  -3.000  -0.2430   0.03010   0.02214  -0.0668   1.0019   0.3571
  -2.750  -0.2186   0.03036   0.02242  -0.0671   1.0019   0.3801
  -2.500  -0.1931   0.03059   0.02264  -0.0676   1.0019   0.3984
  -2.250  -0.1674   0.03086   0.02293  -0.0681   1.0019   0.4180
  -2.000  -0.1417   0.03114   0.02332  -0.0686   1.0019   0.4423
  -1.750  -0.1154   0.03145   0.02387  -0.0692   1.0019   0.4771
  -1.500  -0.0870   0.03176   0.02466  -0.0700   1.0019   0.5456
  -1.250  -0.0705   0.03264   0.02633  -0.0667   0.9990   0.6813
  -1.000  -0.0380   0.03471   0.02834  -0.0666   0.9906   0.7882
  -0.750  -0.0168   0.03584   0.02941  -0.0642   0.9769   0.8302
  -0.500   0.0220   0.03638   0.02980  -0.0638   0.9415   0.8701
  -0.250   0.0438   0.03628   0.02961  -0.0611   0.9222   0.9013
   0.000   0.0584   0.03596   0.02921  -0.0576   0.9083   0.9299
   0.250   0.0793   0.03565   0.02883  -0.0558   0.8958   0.9603
   0.500   0.1147   0.03539   0.02848  -0.0576   0.8824   0.9981
   0.750   0.1596   0.03580   0.02875  -0.0614   0.8737   0.9981
   1.000   0.1913   0.03592   0.02879  -0.0631   0.8618   0.9981
   1.250   0.2274   0.03612   0.02889  -0.0653   0.8513   0.9981
   1.500   0.2753   0.03632   0.02900  -0.0692   0.8442   0.9981
   1.750   0.3061   0.03634   0.02896  -0.0705   0.8322   0.9981
   2.000   0.3430   0.03634   0.02892  -0.0725   0.8221   0.9981
   2.250   0.3905   0.03611   0.02864  -0.0760   0.8148   0.9981
   2.500   0.4221   0.03595   0.02845  -0.0771   0.8027   0.9981
   2.750   0.4754   0.03533   0.02780  -0.0810   0.7980   0.9981
   3.000   0.5041   0.03507   0.02754  -0.0815   0.7850   0.9981
   3.250   0.5364   0.03474   0.02724  -0.0823   0.7732   0.9981
   3.500   0.5849   0.03382   0.02632  -0.0852   0.7677   0.9981
   3.750   0.6144   0.03348   0.02601  -0.0856   0.7548   0.9981
   4.000   0.6645   0.03223   0.02481  -0.0884   0.7503   0.9981
   4.250   0.6933   0.03179   0.02442  -0.0885   0.7367   0.9981
   4.500   0.7437   0.03019   0.02288  -0.0910   0.7328   0.9981
   4.750   0.7723   0.02960   0.02235  -0.0908   0.7187   0.9981
   5.000   0.8233   0.02766   0.02049  -0.0931   0.7147   0.9981
   5.250   0.8550   0.02684   0.01974  -0.0932   0.6997   0.9981
   5.500   0.8936   0.02567   0.01864  -0.0940   0.6853   0.9981
   5.750   0.9396   0.02419   0.01722  -0.0959   0.6696   0.9981
   6.000   0.9868   0.02288   0.01592  -0.0980   0.6473   0.9981
   6.250   1.0421   0.02159   0.01452  -0.1015   0.6181   0.9981
   6.500   1.0803   0.02136   0.01413  -0.1028   0.5808   0.9981
   6.750   1.1106   0.02164   0.01423  -0.1031   0.5432   0.9981
   7.000   1.1381   0.02217   0.01456  -0.1032   0.5093   0.9981
   7.250   1.1658   0.02282   0.01499  -0.1033   0.4801   0.9981
   7.500   1.1931   0.02358   0.01558  -0.1036   0.4550   0.9981
   7.750   1.2186   0.02438   0.01630  -0.1036   0.4336   0.9981
   8.000   1.2469   0.02521   0.01702  -0.1042   0.4151   0.9981
   8.250   1.2704   0.02603   0.01788  -0.1039   0.3989   0.9981
   8.500   1.2952   0.02691   0.01881  -0.1039   0.3845   0.9981
   8.750   1.3247   0.02781   0.01969  -0.1047   0.3715   0.9981
   9.000   1.3508   0.02867   0.02057  -0.1049   0.3592   0.9981
   9.250   1.3722   0.02962   0.02165  -0.1044   0.3479   0.9981
   9.500   1.4041   0.03053   0.02249  -0.1056   0.3359   0.9981
   9.750   1.4137   0.03139   0.02359  -0.1030   0.3255   0.9981
  10.000   1.4365   0.03228   0.02448  -0.1027   0.3142   0.9981
  10.250   1.4471   0.03307   0.02539  -0.1004   0.3033   0.9981
  10.500   1.4582   0.03396   0.02639  -0.0982   0.2923   0.9981
  10.750   1.4701   0.03463   0.02696  -0.0962   0.2792   0.9981
  11.000   1.4635   0.03545   0.02801  -0.0913   0.2680   0.9981
  11.250   1.4606   0.03631   0.02893  -0.0873   0.2556   0.9981
  11.500   1.4572   0.03720   0.02979  -0.0833   0.2428   0.9981
  11.750   1.4505   0.03833   0.03107  -0.0792   0.2308   0.9981
  12.000   1.4468   0.03963   0.03255  -0.0756   0.2192   0.9981
  12.250   1.4439   0.04102   0.03405  -0.0724   0.2076   0.9981
  12.500   1.4380   0.04265   0.03579  -0.0691   0.1947   0.9981
  12.750   1.4294   0.04464   0.03796  -0.0659   0.1786   0.9981
  13.000   1.4173   0.04720   0.04060  -0.0629   0.1570   0.9981
  13.250   1.3998   0.05084   0.04417  -0.0601   0.1188   0.9981
  13.500   1.3758   0.05561   0.04861  -0.0574   0.0900   0.9981
  13.750   1.3522   0.06076   0.05360  -0.0553   0.0739   0.9981
  14.000   1.3330   0.06575   0.05858  -0.0539   0.0649   0.9981
  14.250   1.3167   0.07065   0.06352  -0.0531   0.0592   0.9981
  14.500   1.3028   0.07545   0.06840  -0.0527   0.0547   0.9981
  14.750   1.2915   0.08000   0.07299  -0.0525   0.0516   0.9981
  15.000   1.2836   0.08415   0.07718  -0.0524   0.0486   0.9981
  15.250   1.2800   0.08769   0.08077  -0.0520   0.0459   0.9981
  15.500   1.2815   0.09031   0.08331  -0.0514   0.0435   0.9981
  15.750   1.2843   0.09304   0.08615  -0.0508   0.0410   0.9981
  16.000   1.2917   0.09485   0.08789  -0.0499   0.0387   0.9981
  16.250   1.2939   0.09784   0.09105  -0.0499   0.0369   0.9981
  16.500   1.3051   0.09921   0.09232  -0.0490   0.0349   0.9981
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