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BE50 (original) (be50-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: BE50 (original) (be50-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.08 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-be50-il-1000000-n5.txt
Download as CSV file: xf-be50-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4668   0.13830   0.13661  -0.0002   1.0000   0.0033
 -10.500  -0.6310   0.02457   0.02213  -0.0948   0.9959   0.0050
 -10.250  -0.6011   0.01977   0.01680  -0.0997   0.9945   0.0053
 -10.000  -0.5710   0.01769   0.01440  -0.1018   0.9925   0.0057
  -9.750  -0.5399   0.01617   0.01263  -0.1036   0.9905   0.0060
  -9.500  -0.5085   0.01498   0.01123  -0.1050   0.9883   0.0062
  -9.250  -0.4770   0.01400   0.01010  -0.1063   0.9865   0.0070
  -9.000  -0.4475   0.01330   0.00931  -0.1070   0.9841   0.0077
  -8.750  -0.4184   0.01271   0.00862  -0.1075   0.9814   0.0085
  -8.500  -0.3888   0.01216   0.00797  -0.1080   0.9789   0.0093
  -8.250  -0.3585   0.01217   0.00802  -0.1084   0.9765   0.0104
  -8.000  -0.3301   0.01212   0.00798  -0.1084   0.9729   0.0114
  -7.750  -0.3017   0.01186   0.00766  -0.1085   0.9692   0.0123
  -7.500  -0.2731   0.01159   0.00731  -0.1086   0.9656   0.0129
  -7.250  -0.2454   0.01120   0.00684  -0.1086   0.9609   0.0134
  -7.000  -0.2180   0.01109   0.00673  -0.1084   0.9550   0.0141
  -6.750  -0.1905   0.01119   0.00684  -0.1081   0.9498   0.0147
  -6.500  -0.1631   0.01113   0.00677  -0.1079   0.9438   0.0153
  -6.250  -0.1359   0.01088   0.00645  -0.1076   0.9371   0.0160
  -6.000  -0.1083   0.01063   0.00614  -0.1075   0.9290   0.0167
  -5.750  -0.0808   0.01040   0.00583  -0.1073   0.9214   0.0174
  -5.500  -0.0532   0.01008   0.00542  -0.1071   0.9110   0.0178
  -5.250  -0.0260   0.00988   0.00514  -0.1068   0.8960   0.0182
  -5.000   0.0011   0.00964   0.00477  -0.1065   0.8754   0.0185
  -4.750   0.0281   0.00937   0.00434  -0.1061   0.8498   0.0186
  -4.500   0.0555   0.00892   0.00368  -0.1059   0.8197   0.0192
  -4.250   0.0835   0.00838   0.00292  -0.1059   0.7923   0.0201
  -4.000   0.1115   0.00816   0.00255  -0.1059   0.7667   0.0209
  -3.750   0.1395   0.00805   0.00229  -0.1058   0.7402   0.0215
  -3.500   0.1677   0.00795   0.00207  -0.1058   0.7177   0.0221
  -3.250   0.1960   0.00788   0.00189  -0.1058   0.6979   0.0226
  -3.000   0.2243   0.00780   0.00171  -0.1058   0.6807   0.0231
  -2.750   0.2527   0.00774   0.00155  -0.1058   0.6628   0.0236
  -2.500   0.2811   0.00770   0.00142  -0.1059   0.6433   0.0240
  -2.250   0.3095   0.00767   0.00130  -0.1059   0.6260   0.0246
  -2.000   0.3378   0.00766   0.00120  -0.1059   0.6082   0.0255
  -1.750   0.3660   0.00767   0.00112  -0.1059   0.5885   0.0266
  -1.500   0.3942   0.00770   0.00106  -0.1059   0.5665   0.0275
  -1.250   0.4223   0.00774   0.00101  -0.1059   0.5451   0.0314
  -1.000   0.4505   0.00777   0.00099  -0.1059   0.5267   0.0412
  -0.750   0.4789   0.00768   0.00099  -0.1061   0.5098   0.0952
  -0.500   0.5070   0.00766   0.00102  -0.1062   0.4896   0.1394
  -0.250   0.5346   0.00779   0.00106  -0.1062   0.4431   0.1688
   0.000   0.5615   0.00804   0.00114  -0.1062   0.3897   0.2001
   0.250   0.5895   0.00794   0.00125  -0.1065   0.3650   0.3223
   0.750   0.6455   0.00794   0.00147  -0.1068   0.3372   0.4631
   1.000   0.6736   0.00795   0.00157  -0.1068   0.3289   0.5128
   1.250   0.7015   0.00798   0.00167  -0.1069   0.3198   0.5581
   1.750   0.7508   0.00729   0.00187  -0.1055   0.3013   1.0000
   2.000   0.7785   0.00745   0.00197  -0.1055   0.2907   1.0000
   2.250   0.8064   0.00758   0.00206  -0.1055   0.2813   1.0000
   2.500   0.8341   0.00772   0.00216  -0.1055   0.2731   1.0000
   2.750   0.8617   0.00786   0.00228  -0.1055   0.2639   1.0000
   3.000   0.8888   0.00809   0.00241  -0.1054   0.2437   1.0000
   3.250   0.9159   0.00832   0.00255  -0.1053   0.2261   1.0000
   3.500   0.9425   0.00861   0.00274  -0.1052   0.2047   1.0000
   3.750   0.9687   0.00896   0.00297  -0.1050   0.1792   1.0000
   4.000   0.9950   0.00929   0.00319  -0.1049   0.1587   1.0000
   4.250   1.0201   0.00980   0.00351  -0.1046   0.1240   1.0000
   4.500   1.0415   0.01092   0.00419  -0.1038   0.0455   1.0000
   4.750   1.0666   0.01143   0.00460  -0.1035   0.0233   1.0000
   5.000   1.0918   0.01189   0.00500  -0.1031   0.0108   1.0000
   5.250   1.1175   0.01225   0.00537  -0.1028   0.0087   1.0000
   5.500   1.1433   0.01259   0.00574  -0.1025   0.0076   1.0000
   5.750   1.1690   0.01291   0.00611  -0.1022   0.0070   1.0000
   6.000   1.1945   0.01327   0.00650  -0.1019   0.0064   1.0000
   6.250   1.2195   0.01366   0.00693  -0.1016   0.0058   1.0000
   6.500   1.2437   0.01419   0.00749  -0.1011   0.0051   1.0000
   6.750   1.2682   0.01463   0.00798  -0.1006   0.0048   1.0000
   7.000   1.2925   0.01508   0.00847  -0.1002   0.0045   1.0000
   7.250   1.3164   0.01557   0.00903  -0.0996   0.0042   1.0000
   7.500   1.3399   0.01609   0.00959  -0.0991   0.0040   1.0000
   7.750   1.3631   0.01663   0.01018  -0.0985   0.0037   1.0000
   8.000   1.3858   0.01719   0.01079  -0.0978   0.0035   1.0000
   8.250   1.4076   0.01784   0.01149  -0.0971   0.0034   1.0000
   8.500   1.4271   0.01876   0.01250  -0.0959   0.0031   1.0000
   8.750   1.4462   0.01967   0.01353  -0.0947   0.0030   1.0000
   9.000   1.4663   0.02039   0.01432  -0.0938   0.0029   1.0000
   9.250   1.4858   0.02113   0.01515  -0.0927   0.0028   1.0000
   9.500   1.5044   0.02191   0.01601  -0.0915   0.0027   1.0000
   9.750   1.5221   0.02274   0.01692  -0.0902   0.0026   1.0000
  10.000   1.5387   0.02362   0.01789  -0.0888   0.0024   1.0000
  10.250   1.5535   0.02459   0.01895  -0.0871   0.0023   1.0000
  10.500   1.5669   0.02562   0.02007  -0.0853   0.0023   1.0000
  10.750   1.5784   0.02667   0.02122  -0.0832   0.0022   1.0000
  11.000   1.5861   0.02773   0.02239  -0.0805   0.0021   1.0000
  11.250   1.5919   0.02888   0.02363  -0.0776   0.0021   1.0000
  11.500   1.5962   0.03021   0.02506  -0.0749   0.0021   1.0000
  11.750   1.5998   0.03167   0.02663  -0.0723   0.0020   1.0000
  12.000   1.6015   0.03340   0.02847  -0.0700   0.0020   1.0000
  12.250   1.6026   0.03533   0.03051  -0.0679   0.0019   1.0000
  12.500   1.6012   0.03764   0.03295  -0.0662   0.0019   1.0000
  12.750   1.5981   0.04037   0.03581  -0.0648   0.0019   1.0000
  13.000   1.5926   0.04362   0.03920  -0.0641   0.0019   1.0000
  13.250   1.5847   0.04750   0.04323  -0.0639   0.0018   1.0000
  13.500   1.5749   0.05195   0.04783  -0.0644   0.0018   1.0000
  13.750   1.5616   0.05721   0.05326  -0.0656   0.0018   1.0000
  14.000   1.5480   0.06278   0.05899  -0.0672   0.0018   1.0000
  14.250   1.5311   0.06916   0.06553  -0.0693   0.0018   1.0000
  14.500   1.5141   0.07577   0.07229  -0.0717   0.0018   1.0000
  14.750   1.4959   0.08284   0.07952  -0.0745   0.0017   1.0000
  15.000   1.4774   0.09028   0.08710  -0.0777   0.0017   1.0000
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