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BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BE50 (smoothed) (be50sm-il)
Reynolds number: 50,000
Max Cl/Cd: 43.02 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-be50sm-il-50000-n5.txt
Download as CSV file: xf-be50sm-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3626   0.09643   0.08975  -0.0219   1.0000   0.1008
  -7.000  -0.3599   0.09367   0.08708  -0.0230   1.0000   0.1027
  -6.750  -0.3595   0.09137   0.08488  -0.0265   1.0000   0.1063
  -6.250  -0.3416   0.08109   0.07461  -0.0380   1.0000   0.0659
  -6.000  -0.3350   0.07784   0.07141  -0.0359   1.0000   0.0646
  -5.750  -0.3261   0.07432   0.06792  -0.0370   1.0000   0.0634
  -5.500  -0.3150   0.07056   0.06418  -0.0392   1.0000   0.0619
  -5.000  -0.2641   0.05742   0.05059  -0.0562   1.0000   0.0530
  -4.750  -0.2462   0.05359   0.04665  -0.0578   1.0000   0.0524
  -4.500  -0.2225   0.04921   0.04209  -0.0611   1.0000   0.0518
  -4.250  -0.1939   0.04453   0.03706  -0.0653   1.0000   0.0516
  -4.000  -0.1597   0.03967   0.03161  -0.0700   1.0000   0.0524
  -3.750  -0.1342   0.03698   0.02874  -0.0717   1.0000   0.0559
  -3.500  -0.1048   0.03427   0.02565  -0.0736   1.0000   0.0589
  -3.250  -0.0715   0.03118   0.02197  -0.0758   1.0000   0.0608
  -3.000  -0.0385   0.02868   0.01874  -0.0773   1.0000   0.0648
  -2.750  -0.0107   0.02720   0.01706  -0.0780   1.0000   0.0714
  -2.500   0.0184   0.02568   0.01513  -0.0784   1.0000   0.0768
  -2.250   0.0463   0.02454   0.01379  -0.0787   1.0000   0.0848
  -2.000   0.0740   0.02368   0.01274  -0.0789   1.0000   0.0969
  -1.750   0.1026   0.02294   0.01180  -0.0792   1.0000   0.1112
  -1.500   0.1310   0.02240   0.01116  -0.0797   1.0000   0.1350
  -1.250   0.1599   0.02185   0.01071  -0.0804   1.0000   0.1722
  -1.000   0.2037   0.02098   0.01027  -0.0842   0.9938   0.2701
  -0.750   0.2457   0.02001   0.01022  -0.0873   0.9852   0.5179
  -0.500   0.2779   0.01886   0.00987  -0.0874   0.9701   1.0000
  -0.250   0.3231   0.01905   0.00963  -0.0908   0.9559   1.0000
   0.000   0.3652   0.01917   0.00943  -0.0936   0.9405   1.0000
   0.250   0.4061   0.01927   0.00928  -0.0960   0.9254   1.0000
   0.500   0.4459   0.01933   0.00916  -0.0981   0.9103   1.0000
   0.750   0.4831   0.01936   0.00904  -0.0996   0.8944   1.0000
   1.000   0.5186   0.01935   0.00893  -0.1006   0.8778   1.0000
   1.250   0.5535   0.01932   0.00881  -0.1014   0.8607   1.0000
   1.500   0.5881   0.01925   0.00867  -0.1019   0.8434   1.0000
   1.750   0.6179   0.01926   0.00864  -0.1017   0.8224   1.0000
   2.000   0.6498   0.01920   0.00853  -0.1016   0.8022   1.0000
   2.250   0.6790   0.01921   0.00853  -0.1011   0.7789   1.0000
   2.500   0.7087   0.01921   0.00848  -0.1005   0.7552   1.0000
   2.750   0.7378   0.01924   0.00845  -0.0998   0.7298   1.0000
   3.000   0.7652   0.01934   0.00850  -0.0989   0.7019   1.0000
   3.250   0.7922   0.01951   0.00863  -0.0980   0.6728   1.0000
   3.500   0.8180   0.01975   0.00880  -0.0969   0.6423   1.0000
   3.750   0.8438   0.02007   0.00903  -0.0959   0.6116   1.0000
   4.000   0.8691   0.02045   0.00933  -0.0949   0.5814   1.0000
   4.250   0.8942   0.02089   0.00975  -0.0940   0.5525   1.0000
   4.500   0.9191   0.02140   0.01018  -0.0931   0.5255   1.0000
   4.750   0.9439   0.02194   0.01066  -0.0923   0.5008   1.0000
   5.000   0.9686   0.02253   0.01125  -0.0915   0.4773   1.0000
   5.250   0.9934   0.02316   0.01186  -0.0908   0.4562   1.0000
   5.500   1.0182   0.02382   0.01262  -0.0902   0.4362   1.0000
   5.750   1.0429   0.02451   0.01334  -0.0895   0.4181   1.0000
   6.000   1.0676   0.02524   0.01412  -0.0888   0.4012   1.0000
   6.250   1.0918   0.02601   0.01501  -0.0882   0.3843   1.0000
   6.500   1.1159   0.02681   0.01600  -0.0875   0.3683   1.0000
   6.750   1.1395   0.02764   0.01698  -0.0867   0.3526   1.0000
   7.000   1.1627   0.02850   0.01801  -0.0859   0.3372   1.0000
   7.250   1.1853   0.02937   0.01906  -0.0850   0.3214   1.0000
   7.500   1.2068   0.03023   0.02010  -0.0839   0.3049   1.0000
   7.750   1.2261   0.03104   0.02115  -0.0826   0.2858   1.0000
   8.000   1.2409   0.03166   0.02190  -0.0807   0.2605   1.0000
   8.250   1.2522   0.03233   0.02272  -0.0785   0.2292   1.0000
   8.500   1.2633   0.03322   0.02375  -0.0765   0.1947   1.0000
   8.750   1.2727   0.03453   0.02505  -0.0744   0.1551   1.0000
   9.000   1.2782   0.03659   0.02691  -0.0721   0.1148   1.0000
   9.250   1.2807   0.03921   0.02931  -0.0697   0.0884   1.0000
   9.500   1.2820   0.04189   0.03194  -0.0672   0.0751   1.0000
   9.750   1.2824   0.04445   0.03464  -0.0645   0.0663   1.0000
  10.000   1.2793   0.04714   0.03733  -0.0619   0.0607   1.0000
  10.250   1.2796   0.04978   0.04022  -0.0597   0.0555   1.0000
  10.500   1.2778   0.05265   0.04322  -0.0578   0.0524   1.0000
  10.750   1.2751   0.05578   0.04640  -0.0560   0.0502   1.0000
  11.000   1.2773   0.05882   0.04975  -0.0545   0.0478   1.0000
  11.250   1.2770   0.06212   0.05334  -0.0533   0.0453   1.0000
  11.500   1.2741   0.06564   0.05708  -0.0526   0.0432   1.0000
  11.750   1.2699   0.06934   0.06091  -0.0523   0.0413   1.0000
  12.000   1.2666   0.07315   0.06478  -0.0520   0.0397   1.0000
  12.250   1.2615   0.07757   0.06944  -0.0521   0.0388   1.0000
  12.500   1.2532   0.08259   0.07479  -0.0530   0.0383   1.0000
  12.750   1.2422   0.08819   0.08069  -0.0547   0.0379   1.0000
  13.000   1.2286   0.09443   0.08720  -0.0571   0.0378   1.0000
  13.250   1.2133   0.10131   0.09433  -0.0604   0.0377   1.0000
  13.500   1.1968   0.10882   0.10206  -0.0645   0.0378   1.0000
  13.750   1.1792   0.11703   0.11047  -0.0692   0.0379   1.0000
  14.000   1.1613   0.12586   0.11946  -0.0745   0.0382   1.0000
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