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BE50 (original) (be50-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: BE50 (original) (be50-il)
Reynolds number: 500,000
Max Cl/Cd: 95.39 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-be50-il-500000-n5.txt
Download as CSV file: xf-be50-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3933   0.08561   0.08343  -0.0234   1.0000   0.0082
  -8.500  -0.4019   0.08221   0.08009  -0.0232   1.0000   0.0085
  -8.250  -0.4110   0.07833   0.07626  -0.0239   1.0000   0.0088
  -8.000  -0.3932   0.06828   0.06621  -0.0378   0.9951   0.0092
  -7.750  -0.3664   0.06356   0.06146  -0.0461   0.9913   0.0095
  -7.500  -0.2998   0.01911   0.01509  -0.1007   0.9849   0.0133
  -7.250  -0.2686   0.01934   0.01538  -0.1014   0.9820   0.0139
  -7.000  -0.2367   0.01941   0.01544  -0.1024   0.9794   0.0146
  -6.750  -0.2040   0.01847   0.01430  -0.1040   0.9772   0.0156
  -6.500  -0.1723   0.01731   0.01290  -0.1053   0.9747   0.0170
  -6.250  -0.1422   0.01662   0.01203  -0.1059   0.9701   0.0181
  -6.000  -0.1102   0.01617   0.01142  -0.1068   0.9659   0.0187
  -5.750  -0.0800   0.01395   0.00885  -0.1081   0.9609   0.0201
  -5.500  -0.0509   0.01342   0.00824  -0.1085   0.9549   0.0211
  -5.250  -0.0213   0.01279   0.00749  -0.1088   0.9491   0.0218
  -5.000   0.0069   0.01213   0.00669  -0.1089   0.9414   0.0224
  -4.750   0.0353   0.01159   0.00605  -0.1089   0.9338   0.0233
  -4.500   0.0633   0.01106   0.00540  -0.1088   0.9246   0.0241
  -4.250   0.0911   0.01050   0.00474  -0.1086   0.9133   0.0247
  -4.000   0.1187   0.01004   0.00418  -0.1083   0.8985   0.0253
  -3.750   0.1461   0.00966   0.00368  -0.1080   0.8808   0.0259
  -3.500   0.1736   0.00936   0.00326  -0.1076   0.8603   0.0265
  -3.250   0.2007   0.00913   0.00289  -0.1072   0.8357   0.0270
  -3.000   0.2279   0.00897   0.00258  -0.1069   0.8092   0.0273
  -2.750   0.2551   0.00887   0.00230  -0.1065   0.7814   0.0277
  -2.500   0.2827   0.00876   0.00204  -0.1063   0.7554   0.0285
  -2.250   0.3106   0.00864   0.00176  -0.1062   0.7332   0.0304
  -2.000   0.3384   0.00860   0.00157  -0.1060   0.7114   0.0323
  -1.750   0.3663   0.00857   0.00145  -0.1059   0.6911   0.0357
  -1.500   0.3942   0.00857   0.00137  -0.1058   0.6716   0.0412
  -1.250   0.4222   0.00845   0.00131  -0.1059   0.6525   0.0865
  -1.000   0.4503   0.00834   0.00131  -0.1060   0.6337   0.1469
  -0.750   0.4782   0.00832   0.00131  -0.1060   0.6154   0.1816
  -0.500   0.5061   0.00828   0.00132  -0.1060   0.5959   0.2289
  -0.250   0.5341   0.00803   0.00143  -0.1063   0.5746   0.3949
   0.250   0.5890   0.00803   0.00159  -0.1063   0.5259   0.5352
   0.500   0.6162   0.00803   0.00167  -0.1062   0.5016   0.5984
   0.750   0.6358   0.00733   0.00171  -0.1042   0.4758   1.0000
   1.000   0.6625   0.00763   0.00178  -0.1040   0.4268   1.0000
   1.250   0.6891   0.00797   0.00190  -0.1038   0.3895   1.0000
   1.500   0.7162   0.00823   0.00203  -0.1037   0.3678   1.0000
   1.750   0.7435   0.00845   0.00216  -0.1037   0.3538   1.0000
   2.000   0.7708   0.00865   0.00230  -0.1036   0.3420   1.0000
   2.250   0.7981   0.00885   0.00244  -0.1035   0.3315   1.0000
   2.500   0.8256   0.00903   0.00259  -0.1034   0.3229   1.0000
   2.750   0.8529   0.00921   0.00276  -0.1034   0.3153   1.0000
   3.000   0.8800   0.00941   0.00292  -0.1033   0.3057   1.0000
   3.250   0.9073   0.00960   0.00309  -0.1032   0.2955   1.0000
   3.500   0.9342   0.00982   0.00327  -0.1031   0.2810   1.0000
   3.750   0.9606   0.01010   0.00347  -0.1029   0.2605   1.0000
   4.000   0.9873   0.01035   0.00367  -0.1028   0.2419   1.0000
   4.250   1.0132   0.01069   0.00390  -0.1026   0.2176   1.0000
   4.500   1.0388   0.01108   0.00417  -0.1024   0.1930   1.0000
   4.750   1.0630   0.01167   0.00457  -0.1020   0.1543   1.0000
   5.000   1.0859   0.01244   0.00506  -0.1014   0.1060   1.0000
   5.250   1.1056   0.01377   0.00593  -0.1005   0.0326   1.0000
   5.500   1.1291   0.01446   0.00652  -0.0999   0.0140   1.0000
   5.750   1.1538   0.01492   0.00702  -0.0994   0.0109   1.0000
   6.000   1.1783   0.01541   0.00761  -0.0989   0.0095   1.0000
   6.250   1.2021   0.01600   0.00828  -0.0983   0.0085   1.0000
   6.500   1.2248   0.01674   0.00913  -0.0976   0.0076   1.0000
   6.750   1.2482   0.01732   0.00979  -0.0969   0.0073   1.0000
   7.000   1.2709   0.01797   0.01053  -0.0962   0.0069   1.0000
   7.250   1.2931   0.01864   0.01130  -0.0954   0.0063   1.0000
   7.500   1.3147   0.01935   0.01208  -0.0946   0.0057   1.0000
   7.750   1.3348   0.02022   0.01303  -0.0936   0.0054   1.0000
   8.000   1.3523   0.02137   0.01428  -0.0922   0.0051   1.0000
   8.250   1.3675   0.02270   0.01572  -0.0905   0.0049   1.0000
   8.500   1.3851   0.02366   0.01679  -0.0891   0.0048   1.0000
   8.750   1.4011   0.02475   0.01798  -0.0875   0.0046   1.0000
   9.000   1.4153   0.02595   0.01933  -0.0857   0.0044   1.0000
   9.250   1.4277   0.02724   0.02075  -0.0837   0.0043   1.0000
   9.500   1.4383   0.02862   0.02226  -0.0815   0.0041   1.0000
   9.750   1.4459   0.03006   0.02382  -0.0788   0.0040   1.0000
  10.000   1.4502   0.03154   0.02543  -0.0757   0.0039   1.0000
  10.250   1.4541   0.03311   0.02713  -0.0729   0.0038   1.0000
  10.500   1.4578   0.03473   0.02889  -0.0704   0.0037   1.0000
  10.750   1.4611   0.03646   0.03074  -0.0681   0.0036   1.0000
  11.000   1.4637   0.03833   0.03273  -0.0662   0.0035   1.0000
  11.250   1.4656   0.04036   0.03487  -0.0646   0.0034   1.0000
  11.500   1.4651   0.04280   0.03744  -0.0632   0.0033   1.0000
  11.750   1.4629   0.04560   0.04036  -0.0622   0.0032   1.0000
  12.000   1.4577   0.04900   0.04391  -0.0615   0.0032   1.0000
  12.250   1.4483   0.05317   0.04825  -0.0613   0.0031   1.0000
  12.500   1.4381   0.05770   0.05296  -0.0615   0.0031   1.0000
  12.750   1.4309   0.06207   0.05751  -0.0623   0.0030   1.0000
  13.000   1.4222   0.06688   0.06253  -0.0636   0.0030   1.0000
  13.250   1.4114   0.07216   0.06798  -0.0652   0.0030   1.0000
  13.500   1.3998   0.07782   0.07382  -0.0673   0.0030   1.0000
  13.750   1.3871   0.08391   0.08009  -0.0698   0.0030   1.0000
  14.000   1.3732   0.09041   0.08675  -0.0726   0.0030   1.0000
  14.250   1.3589   0.09733   0.09383  -0.0758   0.0030   1.0000
  14.500   1.3446   0.10452   0.10118  -0.0794   0.0030   1.0000
  14.750   1.3297   0.11199   0.10880  -0.0831   0.0030   1.0000
  15.000   1.3151   0.11961   0.11656  -0.0870   0.0030   1.0000
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