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BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: BE50 (smoothed) (be50sm-il)
Reynolds number: 100,000
Max Cl/Cd: 60.5 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-be50sm-il-100000.txt
Download as CSV file: xf-be50sm-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3577   0.09540   0.09060  -0.0222   1.0000   0.0762
  -7.250  -0.3637   0.09396   0.08928  -0.0243   1.0000   0.0786
  -7.000  -0.3655   0.09266   0.08809  -0.0329   1.0000   0.0797
  -6.750  -0.3615   0.08780   0.08329  -0.0296   1.0000   0.0812
  -6.500  -0.3535   0.08453   0.08005  -0.0250   1.0000   0.0841
  -6.250  -0.3489   0.08187   0.07744  -0.0251   1.0000   0.0871
  -6.000  -0.3439   0.07919   0.07478  -0.0281   1.0000   0.0912
  -5.750  -0.3299   0.07521   0.07081  -0.0406   1.0000   0.0946
  -5.500  -0.3288   0.07223   0.06789  -0.0343   1.0000   0.0963
  -5.250  -0.3221   0.06965   0.06534  -0.0325   1.0000   0.0995
  -5.000  -0.2914   0.06482   0.06032  -0.0468   1.0000   0.1087
  -4.750  -0.2893   0.06212   0.05775  -0.0416   1.0000   0.1106
  -4.500  -0.2786   0.05962   0.05527  -0.0405   1.0000   0.1154
  -4.250  -0.2515   0.05521   0.05073  -0.0474   1.0000   0.1249
  -4.000  -0.2223   0.05149   0.04682  -0.0533   1.0000   0.1379
  -3.750  -0.2124   0.04924   0.04467  -0.0506   1.0000   0.1425
  -3.500  -0.1898   0.04649   0.04183  -0.0526   1.0000   0.1587
  -3.250  -0.1610   0.04343   0.03861  -0.0566   1.0000   0.1824
  -3.000  -0.0560   0.02883   0.02179  -0.0748   1.0000   0.0791
  -2.750  -0.0198   0.02569   0.01816  -0.0770   1.0000   0.0781
  -2.500  -0.0606   0.03376   0.02828  -0.0670   1.0000   0.2116
  -2.250  -0.0464   0.03309   0.02781  -0.0649   1.0000   0.2568
  -2.000   0.0787   0.02077   0.01215  -0.0805   1.0000   0.0958
  -1.750   0.1082   0.01990   0.01115  -0.0810   1.0000   0.1058
  -1.500   0.1372   0.01924   0.01040  -0.0816   1.0000   0.1220
  -1.250   0.1671   0.01850   0.00985  -0.0825   1.0000   0.1470
  -1.000   0.2006   0.01785   0.00946  -0.0842   0.9991   0.2015
  -0.750   0.2538   0.01620   0.00924  -0.0894   0.9951   0.5441
  -0.500   0.2932   0.01522   0.00895  -0.0909   0.9837   1.0000
  -0.250   0.3424   0.01541   0.00882  -0.0954   0.9717   1.0000
   0.000   0.3894   0.01552   0.00869  -0.0992   0.9590   1.0000
   0.250   0.4349   0.01555   0.00856  -0.1026   0.9460   1.0000
   0.500   0.4795   0.01549   0.00837  -0.1056   0.9328   1.0000
   0.750   0.5240   0.01534   0.00813  -0.1084   0.9198   1.0000
   1.000   0.5649   0.01512   0.00786  -0.1102   0.9059   1.0000
   1.250   0.6028   0.01486   0.00756  -0.1113   0.8910   1.0000
   1.500   0.6383   0.01457   0.00724  -0.1118   0.8749   1.0000
   1.750   0.6720   0.01426   0.00690  -0.1117   0.8579   1.0000
   2.000   0.7002   0.01408   0.00671  -0.1107   0.8359   1.0000
   2.250   0.7299   0.01385   0.00642  -0.1098   0.8145   1.0000
   2.500   0.7566   0.01374   0.00625  -0.1084   0.7878   1.0000
   2.750   0.7829   0.01370   0.00613  -0.1070   0.7587   1.0000
   3.000   0.8082   0.01378   0.00613  -0.1055   0.7250   1.0000
   3.250   0.8334   0.01394   0.00614  -0.1041   0.6895   1.0000
   3.500   0.8580   0.01421   0.00625  -0.1027   0.6514   1.0000
   3.750   0.8827   0.01459   0.00641  -0.1015   0.6151   1.0000
   4.000   0.9070   0.01504   0.00674  -0.1004   0.5788   1.0000
   4.250   0.9316   0.01555   0.00708  -0.0994   0.5472   1.0000
   4.500   0.9563   0.01609   0.00748  -0.0986   0.5188   1.0000
   4.750   0.9811   0.01666   0.00795  -0.0979   0.4934   1.0000
   5.000   1.0062   0.01726   0.00844  -0.0972   0.4713   1.0000
   5.250   1.0311   0.01787   0.00907  -0.0965   0.4501   1.0000
   5.500   1.0563   0.01853   0.00965  -0.0959   0.4316   1.0000
   5.750   1.0813   0.01921   0.01034  -0.0954   0.4137   1.0000
   6.000   1.1060   0.01989   0.01107  -0.0947   0.3962   1.0000
   6.250   1.1308   0.02061   0.01186  -0.0941   0.3798   1.0000
   6.500   1.1553   0.02133   0.01263  -0.0935   0.3636   1.0000
   6.750   1.1795   0.02205   0.01339  -0.0928   0.3474   1.0000
   7.000   1.2021   0.02264   0.01404  -0.0918   0.3285   1.0000
   7.250   1.2221   0.02291   0.01438  -0.0905   0.3046   1.0000
   7.500   1.2413   0.02317   0.01480  -0.0890   0.2803   1.0000
   7.750   1.2604   0.02347   0.01522  -0.0876   0.2566   1.0000
   8.000   1.2780   0.02371   0.01564  -0.0860   0.2258   1.0000
   8.250   1.2910   0.02439   0.01622  -0.0839   0.1607   1.0000
   8.500   1.2934   0.02748   0.01859  -0.0805   0.0898   1.0000
   8.750   1.2998   0.02999   0.02092  -0.0775   0.0735   1.0000
   9.000   1.3109   0.03195   0.02293  -0.0752   0.0633   1.0000
   9.250   1.3227   0.03420   0.02530  -0.0728   0.0575   1.0000
   9.500   1.3374   0.03641   0.02755  -0.0708   0.0532   1.0000
   9.750   1.3567   0.03988   0.03094  -0.0697   0.0497   1.0000
  10.000   1.3715   0.04198   0.03343  -0.0677   0.0467   1.0000
  10.250   1.3858   0.04454   0.03624  -0.0660   0.0439   1.0000
  10.500   1.3998   0.04770   0.03966  -0.0643   0.0425   1.0000
  10.750   1.4103   0.05120   0.04345  -0.0625   0.0416   1.0000
  11.000   1.4155   0.05497   0.04757  -0.0602   0.0412   1.0000
  11.250   1.4154   0.05883   0.05176  -0.0577   0.0408   1.0000
  11.500   1.4103   0.06285   0.05609  -0.0551   0.0403   1.0000
  11.750   1.3980   0.06676   0.06027  -0.0520   0.0400   1.0000
  12.000   1.3822   0.07069   0.06448  -0.0493   0.0399   1.0000
  12.250   1.3641   0.07457   0.06864  -0.0473   0.0399   1.0000
  12.500   1.3442   0.07882   0.07315  -0.0463   0.0399   1.0000
  12.750   1.3224   0.08338   0.07800  -0.0465   0.0402   1.0000
  13.000   1.1302   0.08605   0.08131  -0.0361   0.0446   1.0000
  13.250   1.0951   0.09321   0.08867  -0.0390   0.0452   1.0000
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