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BE50 (smoothed) (be50sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: BE50 (smoothed) (be50sm-il)
Reynolds number: 500,000
Max Cl/Cd: 97.79 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-be50sm-il-500000-n5.txt
Download as CSV file: xf-be50sm-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3756   0.09257   0.09029  -0.0218   1.0000   0.0102
  -8.000  -0.3716   0.08958   0.08732  -0.0228   1.0000   0.0099
  -7.750  -0.3702   0.08655   0.08433  -0.0235   1.0000   0.0095
  -7.500  -0.3744   0.08393   0.08175  -0.0229   1.0000   0.0093
  -7.250  -0.3800   0.08129   0.07916  -0.0224   1.0000   0.0090
  -6.250  -0.2374   0.01937   0.01541  -0.1004   0.9800   0.0087
  -6.000  -0.2052   0.01690   0.01248  -0.1025   0.9766   0.0091
  -5.750  -0.1724   0.01515   0.01036  -0.1042   0.9737   0.0095
  -5.500  -0.1394   0.01408   0.00905  -0.1055   0.9711   0.0102
  -5.250  -0.1081   0.01327   0.00803  -0.1064   0.9671   0.0107
  -5.000  -0.0778   0.01211   0.00667  -0.1071   0.9620   0.0112
  -4.750  -0.0462   0.01139   0.00584  -0.1080   0.9578   0.0120
  -4.500  -0.0161   0.01091   0.00527  -0.1084   0.9523   0.0128
  -4.250   0.0135   0.01044   0.00471  -0.1087   0.9458   0.0139
  -4.000   0.0432   0.01003   0.00421  -0.1090   0.9391   0.0151
  -3.750   0.0720   0.00954   0.00364  -0.1090   0.9286   0.0167
  -3.500   0.0996   0.00929   0.00333  -0.1087   0.9134   0.0190
  -3.250   0.1267   0.00911   0.00305  -0.1082   0.8951   0.0213
  -3.000   0.1544   0.00879   0.00265  -0.1080   0.8790   0.0242
  -2.750   0.1821   0.00862   0.00243  -0.1078   0.8637   0.0280
  -2.500   0.2098   0.00846   0.00216  -0.1075   0.8474   0.0318
  -2.250   0.2376   0.00830   0.00195  -0.1073   0.8303   0.0380
  -2.000   0.2653   0.00819   0.00178  -0.1071   0.8121   0.0474
  -1.750   0.2931   0.00810   0.00164  -0.1069   0.7929   0.0598
  -1.500   0.3207   0.00804   0.00152  -0.1067   0.7726   0.0761
  -1.250   0.3484   0.00797   0.00144  -0.1066   0.7516   0.1007
  -0.750   0.4038   0.00787   0.00133  -0.1064   0.7075   0.1698
  -0.500   0.4314   0.00780   0.00130  -0.1063   0.6848   0.2227
  -0.250   0.4591   0.00770   0.00131  -0.1063   0.6609   0.3002
   0.000   0.4867   0.00764   0.00136  -0.1063   0.6362   0.3830
   0.250   0.5141   0.00766   0.00141  -0.1062   0.6114   0.4432
   0.500   0.5414   0.00771   0.00146  -0.1061   0.5854   0.4916
   0.750   0.5686   0.00774   0.00152  -0.1059   0.5579   0.5473
   1.000   0.5956   0.00766   0.00161  -0.1058   0.5292   0.6472
   1.250   0.6148   0.00711   0.00162  -0.1036   0.5012   1.0000
   1.500   0.6419   0.00735   0.00169  -0.1034   0.4708   1.0000
   1.750   0.6689   0.00760   0.00178  -0.1032   0.4415   1.0000
   2.000   0.6959   0.00785   0.00189  -0.1030   0.4154   1.0000
   2.250   0.7231   0.00808   0.00200  -0.1029   0.3934   1.0000
   2.750   0.7773   0.00853   0.00226  -0.1026   0.3582   1.0000
   3.000   0.8045   0.00874   0.00241  -0.1024   0.3434   1.0000
   3.250   0.8316   0.00895   0.00255  -0.1023   0.3302   1.0000
   3.500   0.8588   0.00915   0.00271  -0.1022   0.3179   1.0000
   3.750   0.8859   0.00935   0.00287  -0.1020   0.3061   1.0000
   4.000   0.9129   0.00956   0.00306  -0.1018   0.2956   1.0000
   4.250   0.9398   0.00978   0.00324  -0.1017   0.2850   1.0000
   4.750   0.9934   0.01021   0.00365  -0.1013   0.2643   1.0000
   5.000   1.0200   0.01044   0.00388  -0.1010   0.2545   1.0000
   5.250   1.0464   0.01070   0.00412  -0.1008   0.2442   1.0000
   5.750   1.0979   0.01135   0.00464  -0.1002   0.2061   1.0000
   6.000   1.1226   0.01183   0.00498  -0.0998   0.1762   1.0000
   6.250   1.1475   0.01225   0.00532  -0.0994   0.1544   1.0000
   6.500   1.1720   0.01273   0.00571  -0.0989   0.1325   1.0000
   6.750   1.1953   0.01338   0.00620  -0.0983   0.1018   1.0000
   7.000   1.2170   0.01424   0.00685  -0.0976   0.0654   1.0000
   7.250   1.2386   0.01511   0.00757  -0.0967   0.0385   1.0000
   7.500   1.2613   0.01578   0.00820  -0.0960   0.0261   1.0000
   7.750   1.2843   0.01640   0.00882  -0.0953   0.0199   1.0000
   8.000   1.3070   0.01703   0.00947  -0.0945   0.0162   1.0000
   8.250   1.3296   0.01764   0.01015  -0.0937   0.0139   1.0000
   8.500   1.3522   0.01822   0.01083  -0.0930   0.0125   1.0000
   8.750   1.3737   0.01891   0.01156  -0.0921   0.0111   1.0000
   9.000   1.3939   0.01974   0.01247  -0.0910   0.0098   1.0000
   9.250   1.4152   0.02037   0.01319  -0.0901   0.0091   1.0000
   9.500   1.4353   0.02110   0.01401  -0.0890   0.0084   1.0000
   9.750   1.4546   0.02188   0.01488  -0.0878   0.0078   1.0000
  10.000   1.4723   0.02279   0.01586  -0.0864   0.0073   1.0000
  10.250   1.4856   0.02410   0.01731  -0.0845   0.0067   1.0000
  10.500   1.5012   0.02506   0.01839  -0.0828   0.0065   1.0000
  10.750   1.5156   0.02606   0.01951  -0.0810   0.0062   1.0000
  11.000   1.5285   0.02711   0.02068  -0.0791   0.0058   1.0000
  11.250   1.5390   0.02818   0.02185  -0.0768   0.0055   1.0000
  11.500   1.5468   0.02925   0.02303  -0.0741   0.0052   1.0000
  11.750   1.5540   0.03041   0.02429  -0.0716   0.0049   1.0000
  12.000   1.5593   0.03177   0.02575  -0.0691   0.0047   1.0000
  12.250   1.5618   0.03343   0.02753  -0.0666   0.0045   1.0000
  12.500   1.5596   0.03561   0.02984  -0.0640   0.0044   1.0000
  12.750   1.5528   0.03840   0.03281  -0.0617   0.0042   1.0000
  13.000   1.5497   0.04111   0.03567  -0.0602   0.0042   1.0000
  13.250   1.5474   0.04392   0.03864  -0.0592   0.0041   1.0000
  13.500   1.5436   0.04716   0.04204  -0.0587   0.0041   1.0000
  13.750   1.5381   0.05084   0.04589  -0.0587   0.0040   1.0000
  14.000   1.5312   0.05497   0.05019  -0.0592   0.0039   1.0000
  14.250   1.5224   0.05964   0.05503  -0.0603   0.0039   1.0000
  14.500   1.5118   0.06479   0.06034  -0.0618   0.0039   1.0000
  14.750   1.5004   0.07033   0.06604  -0.0637   0.0038   1.0000
  15.000   1.4869   0.07639   0.07227  -0.0660   0.0038   1.0000
  15.250   1.4726   0.08277   0.07881  -0.0685   0.0038   1.0000
  15.500   1.4568   0.08960   0.08579  -0.0714   0.0037   1.0000
  15.750   1.4415   0.09647   0.09280  -0.0743   0.0037   1.0000
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