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BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: BE50 (smoothed) (be50sm-il)
Reynolds number: 50,000
Max Cl/Cd: 38.93 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-be50sm-il-50000.txt
Download as CSV file: xf-be50sm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BE50 (smoothed)                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3840   0.10714   0.10047  -0.0189   1.0000   0.1649
  -7.500  -0.3649   0.10132   0.09464  -0.0173   1.0000   0.1707
  -7.250  -0.3677   0.09962   0.09305  -0.0176   1.0000   0.1775
  -7.000  -0.3703   0.09736   0.09092  -0.0190   1.0000   0.1814
  -6.750  -0.3616   0.09405   0.08762  -0.0177   1.0000   0.1914
  -6.500  -0.3587   0.09107   0.08474  -0.0178   1.0000   0.1982
  -6.250  -0.3616   0.08999   0.08377  -0.0213   1.0000   0.2083
  -6.000  -0.3515   0.08590   0.07973  -0.0176   1.0000   0.2195
  -5.750  -0.3471   0.08297   0.07688  -0.0171   1.0000   0.2296
  -5.250  -0.3396   0.07786   0.07193  -0.0185   1.0000   0.2547
  -5.000  -0.3338   0.07514   0.06927  -0.0183   1.0000   0.2690
  -4.750  -0.3272   0.07231   0.06650  -0.0171   1.0000   0.2845
  -4.500  -0.3203   0.06955   0.06380  -0.0156   1.0000   0.3017
  -4.250  -0.3125   0.06713   0.06144  -0.0166   1.0000   0.3261
  -4.000  -0.3045   0.06472   0.05907  -0.0153   1.0000   0.3525
  -3.750  -0.2992   0.06175   0.05616  -0.0111   1.0000   0.3749
  -3.500  -0.2944   0.05942   0.05390  -0.0081   1.0000   0.4141
  -3.250  -0.2921   0.05708   0.05165  -0.0032   1.0000   0.4569
  -3.000  -0.1436   0.04445   0.03783  -0.0544   1.0000   0.2451
  -2.750  -0.0467   0.03389   0.02540  -0.0738   1.0000   0.1482
  -2.500  -0.0088   0.03096   0.02180  -0.0766   1.0000   0.1519
  -2.250   0.0246   0.02855   0.01902  -0.0780   1.0000   0.1548
  -2.000   0.0577   0.02680   0.01678  -0.0791   1.0000   0.1666
  -1.750   0.0885   0.02532   0.01506  -0.0798   1.0000   0.1827
  -1.500   0.1193   0.02415   0.01370  -0.0805   1.0000   0.2092
  -1.250   0.1501   0.02302   0.01257  -0.0809   1.0000   0.2490
  -1.000   0.1820   0.02195   0.01182  -0.0815   1.0000   0.3354
  -0.750   0.2063   0.01888   0.01099  -0.0789   1.0000   0.7746
  -0.500   0.2226   0.01914   0.01059  -0.0778   1.0000   1.0000
  -0.250   0.2471   0.01965   0.01067  -0.0780   1.0000   1.0000
   0.000   0.2705   0.02022   0.01094  -0.0783   1.0000   1.0000
   0.250   0.2930   0.02086   0.01134  -0.0785   1.0000   1.0000
   0.500   0.3148   0.02157   0.01185  -0.0788   1.0000   1.0000
   0.750   0.3358   0.02238   0.01250  -0.0791   1.0000   1.0000
   1.000   0.3559   0.02328   0.01329  -0.0795   1.0000   1.0000
   1.250   0.3784   0.02431   0.01423  -0.0805   0.9981   1.0000
   1.500   0.4448   0.02531   0.01510  -0.0891   0.9747   1.0000
   1.750   0.5062   0.02604   0.01576  -0.0962   0.9501   1.0000
   2.000   0.5656   0.02646   0.01618  -0.1023   0.9248   1.0000
   2.250   0.6250   0.02651   0.01627  -0.1077   0.8996   1.0000
   2.500   0.6768   0.02633   0.01619  -0.1111   0.8724   1.0000
   2.750   0.7236   0.02594   0.01589  -0.1129   0.8450   1.0000
   3.000   0.7663   0.02542   0.01545  -0.1136   0.8173   1.0000
   3.250   0.8050   0.02487   0.01500  -0.1132   0.7889   1.0000
   3.500   0.8401   0.02440   0.01457  -0.1121   0.7598   1.0000
   3.750   0.8720   0.02410   0.01426  -0.1106   0.7302   1.0000
   4.000   0.9000   0.02413   0.01427  -0.1088   0.6994   1.0000
   4.250   0.9266   0.02437   0.01454  -0.1071   0.6695   1.0000
   4.500   0.9529   0.02473   0.01487  -0.1055   0.6413   1.0000
   4.750   0.9796   0.02516   0.01524  -0.1041   0.6156   1.0000
   5.000   1.0038   0.02588   0.01599  -0.1028   0.5897   1.0000
   5.250   1.0280   0.02669   0.01691  -0.1016   0.5658   1.0000
   5.500   1.0543   0.02737   0.01755  -0.1005   0.5446   1.0000
   5.750   1.0769   0.02844   0.01877  -0.0994   0.5225   1.0000
   6.000   1.1023   0.02930   0.01966  -0.0983   0.5029   1.0000
   6.250   1.1248   0.03047   0.02099  -0.0972   0.4830   1.0000
   6.500   1.1480   0.03161   0.02232  -0.0961   0.4638   1.0000
   6.750   1.1729   0.03262   0.02338  -0.0949   0.4453   1.0000
   7.000   1.1930   0.03407   0.02509  -0.0937   0.4256   1.0000
   7.250   1.2154   0.03523   0.02640  -0.0923   0.4054   1.0000
   7.500   1.2359   0.03642   0.02775  -0.0906   0.3831   1.0000
   7.750   1.2564   0.03698   0.02841  -0.0885   0.3551   1.0000
   8.000   1.2750   0.03670   0.02802  -0.0858   0.3191   1.0000
   8.250   1.2881   0.03660   0.02791  -0.0827   0.2791   1.0000
   8.500   1.2954   0.03674   0.02784  -0.0788   0.2289   1.0000
   8.750   1.2973   0.03806   0.02869  -0.0745   0.1765   1.0000
   9.000   1.3039   0.04056   0.03113  -0.0713   0.1427   1.0000
   9.250   1.3170   0.04320   0.03353  -0.0692   0.1224   1.0000
   9.500   1.3310   0.04617   0.03667  -0.0673   0.1088   1.0000
   9.750   1.3468   0.04968   0.04050  -0.0655   0.1008   1.0000
  10.000   1.3584   0.05367   0.04481  -0.0636   0.0954   1.0000
  10.250   1.3624   0.05735   0.04895  -0.0613   0.0907   1.0000
  10.500   1.3768   0.06126   0.05276  -0.0603   0.0853   1.0000
  10.750   1.3702   0.06570   0.05777  -0.0575   0.0846   1.0000
  11.000   1.3590   0.07031   0.06285  -0.0548   0.0843   1.0000
  11.250   1.3430   0.07486   0.06775  -0.0523   0.0843   1.0000
  11.500   1.3231   0.07931   0.07249  -0.0500   0.0846   1.0000
  11.750   1.3019   0.08421   0.07761  -0.0489   0.0849   1.0000
  12.000   1.2805   0.08964   0.08323  -0.0489   0.0853   1.0000
  12.250   1.1874   0.10433   0.09841  -0.0599   0.0952   1.0000
  12.500   1.1656   0.11329   0.10739  -0.0645   0.0970   1.0000
  12.750   1.1498   0.12188   0.11593  -0.0687   0.0979   1.0000
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