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BE50 (original) (be50-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: BE50 (original) (be50-il)
Reynolds number: 1,000,000
Max Cl/Cd: 118.18 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-be50-il-1000000.txt
Download as CSV file: xf-be50-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BE50 (original)                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4773   0.14907   0.14735   0.0044   1.0000   0.0086
 -12.750  -0.4706   0.14550   0.14380   0.0029   1.0000   0.0091
 -12.500  -0.4643   0.14146   0.13976   0.0008   1.0000   0.0097
  -7.250  -0.2861   0.01926   0.01614  -0.0975   0.9893   0.0143
  -7.000  -0.2523   0.01918   0.01607  -0.0990   0.9878   0.0148
  -6.750  -0.2172   0.01922   0.01612  -0.1007   0.9864   0.0154
  -6.500  -0.1814   0.01847   0.01526  -0.1029   0.9853   0.0164
  -6.250  -0.1458   0.01675   0.01326  -0.1051   0.9841   0.0177
  -6.000  -0.1131   0.01621   0.01256  -0.1062   0.9817   0.0184
  -5.750  -0.0826   0.01301   0.00889  -0.1079   0.9779   0.0197
  -5.500  -0.0521   0.01262   0.00847  -0.1086   0.9740   0.0208
  -5.250  -0.0217   0.01205   0.00782  -0.1091   0.9702   0.0216
  -5.000   0.0056   0.01124   0.00688  -0.1089   0.9642   0.0222
  -4.750   0.0331   0.01051   0.00604  -0.1087   0.9585   0.0228
  -4.500   0.0603   0.01003   0.00547  -0.1083   0.9522   0.0237
  -4.250   0.0869   0.00963   0.00500  -0.1078   0.9440   0.0245
  -4.000   0.1139   0.00922   0.00451  -0.1074   0.9355   0.0250
  -3.750   0.1407   0.00888   0.00410  -0.1069   0.9260   0.0253
  -3.500   0.1679   0.00859   0.00375  -0.1065   0.9138   0.0255
  -3.250   0.1955   0.00780   0.00284  -0.1063   0.8988   0.0261
  -3.000   0.2232   0.00728   0.00220  -0.1061   0.8780   0.0272
  -2.750   0.2505   0.00705   0.00184  -0.1057   0.8525   0.0290
  -2.500   0.2779   0.00694   0.00159  -0.1054   0.8233   0.0305
  -2.250   0.3053   0.00692   0.00141  -0.1051   0.7922   0.0319
  -2.000   0.3329   0.00692   0.00126  -0.1048   0.7625   0.0334
  -1.750   0.3607   0.00695   0.00116  -0.1047   0.7363   0.0348
  -1.500   0.3889   0.00690   0.00102  -0.1046   0.7140   0.0453
  -1.250   0.4175   0.00662   0.00099  -0.1049   0.6939   0.1479
  -1.000   0.4458   0.00655   0.00099  -0.1050   0.6743   0.2027
  -0.750   0.4741   0.00640   0.00100  -0.1052   0.6547   0.2932
  -0.500   0.5023   0.00628   0.00107  -0.1054   0.6332   0.4029
   0.000   0.5583   0.00629   0.00116  -0.1054   0.5894   0.5023
   0.250   0.5862   0.00620   0.00123  -0.1055   0.5660   0.5962
   0.500   0.6071   0.00543   0.00128  -0.1038   0.5449   1.0000
   0.750   0.6348   0.00561   0.00133  -0.1038   0.5220   1.0000
   1.000   0.6625   0.00580   0.00139  -0.1037   0.4976   1.0000
   1.250   0.6901   0.00601   0.00146  -0.1037   0.4634   1.0000
   1.500   0.7166   0.00639   0.00157  -0.1035   0.4053   1.0000
   1.750   0.7436   0.00669   0.00171  -0.1034   0.3747   1.0000
   2.000   0.7710   0.00691   0.00183  -0.1034   0.3569   1.0000
   2.250   0.7987   0.00708   0.00196  -0.1033   0.3449   1.0000
   2.500   0.8262   0.00726   0.00208  -0.1033   0.3331   1.0000
   2.750   0.8537   0.00745   0.00221  -0.1032   0.3210   1.0000
   3.250   0.9085   0.00781   0.00248  -0.1032   0.2967   1.0000
   3.500   0.9359   0.00798   0.00261  -0.1031   0.2839   1.0000
   3.750   0.9632   0.00815   0.00275  -0.1031   0.2717   1.0000
   4.000   0.9900   0.00840   0.00291  -0.1030   0.2511   1.0000
   4.250   1.0166   0.00868   0.00309  -0.1028   0.2277   1.0000
   4.500   1.0428   0.00901   0.00331  -0.1027   0.2032   1.0000
   4.750   1.0685   0.00940   0.00357  -0.1024   0.1778   1.0000
   5.000   1.0931   0.00997   0.00394  -0.1021   0.1404   1.0000
   5.250   1.1144   0.01106   0.00459  -0.1013   0.0681   1.0000
   5.500   1.1355   0.01220   0.00540  -0.1004   0.0159   1.0000
   5.750   1.1608   0.01263   0.00584  -0.1000   0.0122   1.0000
   6.000   1.1861   0.01304   0.00630  -0.0996   0.0113   1.0000
   6.250   1.2110   0.01351   0.00683  -0.0991   0.0105   1.0000
   6.500   1.2351   0.01408   0.00746  -0.0986   0.0096   1.0000
   6.750   1.2571   0.01498   0.00849  -0.0976   0.0086   1.0000
   7.000   1.2812   0.01546   0.00901  -0.0971   0.0083   1.0000
   7.250   1.3044   0.01608   0.00970  -0.0964   0.0080   1.0000
   7.500   1.3267   0.01678   0.01048  -0.0956   0.0076   1.0000
   7.750   1.3483   0.01753   0.01131  -0.0947   0.0073   1.0000
   8.000   1.3691   0.01833   0.01218  -0.0937   0.0070   1.0000
   8.250   1.3890   0.01919   0.01311  -0.0927   0.0067   1.0000
   8.500   1.4074   0.02019   0.01418  -0.0914   0.0064   1.0000
   8.750   1.4220   0.02157   0.01564  -0.0895   0.0062   1.0000
   9.000   1.4264   0.02412   0.01835  -0.0862   0.0059   1.0000
   9.250   1.4396   0.02558   0.01993  -0.0842   0.0057   1.0000
   9.500   1.4572   0.02637   0.02081  -0.0829   0.0056   1.0000
   9.750   1.4726   0.02732   0.02187  -0.0813   0.0054   1.0000
  10.000   1.4855   0.02849   0.02314  -0.0793   0.0052   1.0000
  10.250   1.4946   0.02983   0.02460  -0.0769   0.0051   1.0000
  10.500   1.4983   0.03137   0.02627  -0.0736   0.0050   1.0000
  10.750   1.5004   0.03311   0.02814  -0.0704   0.0050   1.0000
  11.000   1.5017   0.03499   0.03017  -0.0675   0.0049   1.0000
  11.250   1.5015   0.03709   0.03242  -0.0648   0.0048   1.0000
  11.500   1.4997   0.03946   0.03495  -0.0624   0.0048   1.0000
  11.750   1.4963   0.04211   0.03776  -0.0603   0.0048   1.0000
  12.000   1.4912   0.04511   0.04092  -0.0586   0.0047   1.0000
  12.250   1.4848   0.04846   0.04444  -0.0575   0.0047   1.0000
  12.500   1.4777   0.05207   0.04821  -0.0570   0.0047   1.0000
  12.750   1.4665   0.05656   0.05290  -0.0570   0.0047   1.0000
  13.000   1.4559   0.06117   0.05767  -0.0578   0.0047   1.0000
  13.250   1.4429   0.06647   0.06314  -0.0592   0.0046   1.0000
  13.500   1.4283   0.07226   0.06910  -0.0611   0.0046   1.0000
  13.750   1.4119   0.07867   0.07568  -0.0637   0.0047   1.0000
  14.000   1.3933   0.08584   0.08304  -0.0669   0.0047   1.0000
  14.250   1.3741   0.09348   0.09084  -0.0706   0.0047   1.0000
  14.500   1.3546   0.10168   0.09919  -0.0749   0.0047   1.0000
  14.750   1.3353   0.11024   0.10790  -0.0795   0.0048   1.0000
  15.000   1.3164   0.11899   0.11679  -0.0844   0.0048   1.0000
  15.250   1.2954   0.12855   0.12649  -0.0898   0.0049   1.0000
  15.500   1.2742   0.13854   0.13662  -0.0956   0.0049   1.0000
  15.750   1.2549   0.14850   0.14671  -0.1015   0.0050   1.0000
  16.000   1.2351   0.15928   0.15761  -0.1080   0.0051   1.0000
  16.250   1.2145   0.17112   0.16955  -0.1151   0.0052   1.0000
  16.500   1.1887   0.18578   0.18431  -0.1237   0.0054   1.0000
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