Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

BE50 (original) (be50-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BE50 (original) (be50-il)
Reynolds number: 50,000
Max Cl/Cd: 43.15 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-be50-il-50000-n5.txt
Download as CSV file: xf-be50-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3737   0.10503   0.09820  -0.0193   1.0000   0.1056
  -8.500  -0.3803   0.10367   0.09697  -0.0214   1.0000   0.1089
  -8.250  -0.3858   0.10221   0.09564  -0.0256   1.0000   0.1098
  -8.000  -0.3762   0.09747   0.09096  -0.0239   1.0000   0.1112
  -7.750  -0.3672   0.09373   0.08724  -0.0226   1.0000   0.1135
  -7.500  -0.3617   0.09079   0.08436  -0.0229   1.0000   0.1174
  -7.250  -0.3620   0.08892   0.08259  -0.0298   1.0000   0.1234
  -7.000  -0.3544   0.08497   0.07867  -0.0265   1.0000   0.1273
  -6.750  -0.3472   0.08209   0.07582  -0.0270   1.0000   0.1334
  -6.250  -0.3035   0.06623   0.05967  -0.0503   1.0000   0.0672
  -6.000  -0.2930   0.06299   0.05643  -0.0493   1.0000   0.0659
  -5.750  -0.2758   0.05885   0.05223  -0.0517   1.0000   0.0646
  -5.500  -0.2509   0.05379   0.04697  -0.0570   1.0000   0.0648
  -5.250  -0.2185   0.04809   0.04083  -0.0638   1.0000   0.0663
  -5.000  -0.1893   0.04355   0.03591  -0.0678   1.0000   0.0661
  -4.750  -0.1588   0.03941   0.03133  -0.0713   1.0000   0.0657
  -4.500  -0.1273   0.03577   0.02717  -0.0742   1.0000   0.0658
  -4.250  -0.0953   0.03269   0.02346  -0.0764   1.0000   0.0666
  -4.000  -0.0686   0.03076   0.02131  -0.0775   1.0000   0.0704
  -3.750  -0.0412   0.02917   0.01943  -0.0782   1.0000   0.0740
  -3.500  -0.0115   0.02738   0.01720  -0.0790   1.0000   0.0755
  -3.250   0.0170   0.02594   0.01537  -0.0794   1.0000   0.0774
  -3.000   0.0447   0.02481   0.01388  -0.0796   1.0000   0.0798
  -2.750   0.0717   0.02388   0.01274  -0.0797   1.0000   0.0829
  -2.500   0.0984   0.02325   0.01203  -0.0799   1.0000   0.0886
  -2.250   0.1255   0.02284   0.01150  -0.0802   1.0000   0.1002
  -2.000   0.1657   0.02226   0.01082  -0.0830   0.9942   0.1195
  -1.750   0.2091   0.02145   0.01016  -0.0864   0.9872   0.1743
  -1.500   0.2508   0.02025   0.01021  -0.0900   0.9799   0.4417
  -1.250   0.2796   0.01871   0.00990  -0.0893   0.9659   1.0000
  -1.000   0.3248   0.01890   0.00960  -0.0928   0.9517   1.0000
  -0.750   0.3679   0.01899   0.00935  -0.0957   0.9351   1.0000
  -0.500   0.4087   0.01900   0.00910  -0.0979   0.9164   1.0000
  -0.250   0.4480   0.01899   0.00888  -0.0998   0.8994   1.0000
   0.000   0.4842   0.01899   0.00873  -0.1010   0.8835   1.0000
   0.250   0.5190   0.01900   0.00862  -0.1020   0.8682   1.0000
   0.500   0.5524   0.01901   0.00852  -0.1026   0.8520   1.0000
   0.750   0.5835   0.01904   0.00850  -0.1027   0.8339   1.0000
   1.000   0.6155   0.01903   0.00843  -0.1029   0.8159   1.0000
   1.250   0.6478   0.01900   0.00834  -0.1031   0.7977   1.0000
   1.500   0.6773   0.01906   0.00837  -0.1027   0.7765   1.0000
   1.750   0.7075   0.01909   0.00835  -0.1024   0.7551   1.0000
   2.000   0.7357   0.01920   0.00841  -0.1017   0.7313   1.0000
   2.250   0.7638   0.01933   0.00851  -0.1010   0.7068   1.0000
   2.500   0.7908   0.01951   0.00863  -0.1001   0.6807   1.0000
   2.750   0.8165   0.01978   0.00885  -0.0991   0.6524   1.0000
   3.250   0.8672   0.02044   0.00944  -0.0971   0.5934   1.0000
   3.500   0.8919   0.02085   0.00980  -0.0961   0.5635   1.0000
   3.750   0.9166   0.02130   0.01019  -0.0952   0.5356   1.0000
   4.000   0.9411   0.02182   0.01073  -0.0943   0.5090   1.0000
   4.250   0.9656   0.02238   0.01131  -0.0936   0.4839   1.0000
   4.500   0.9901   0.02296   0.01190  -0.0929   0.4612   1.0000
   4.750   1.0146   0.02357   0.01257  -0.0922   0.4402   1.0000
   5.000   1.0391   0.02420   0.01327  -0.0915   0.4218   1.0000
   5.250   1.0637   0.02490   0.01402  -0.0909   0.4044   1.0000
   5.500   1.0882   0.02567   0.01489  -0.0903   0.3877   1.0000
   5.750   1.1126   0.02649   0.01585  -0.0897   0.3718   1.0000
   6.000   1.1368   0.02738   0.01688  -0.0890   0.3566   1.0000
   6.250   1.1607   0.02830   0.01806  -0.0884   0.3417   1.0000
   6.500   1.1842   0.02927   0.01926  -0.0876   0.3270   1.0000
   6.750   1.2048   0.03012   0.02031  -0.0865   0.3081   1.0000
   7.000   1.2185   0.03064   0.02099  -0.0844   0.2782   1.0000
   7.250   1.2262   0.03104   0.02144  -0.0819   0.2337   1.0000
   7.500   1.2352   0.03203   0.02230  -0.0798   0.1775   1.0000
   7.750   1.2420   0.03415   0.02399  -0.0778   0.1001   1.0000
   8.000   1.2438   0.03733   0.02676  -0.0754   0.0615   1.0000
   8.250   1.2475   0.04008   0.02953  -0.0730   0.0512   1.0000
   8.500   1.2486   0.04280   0.03232  -0.0705   0.0465   1.0000
   8.750   1.2498   0.04521   0.03497  -0.0678   0.0430   1.0000
   9.000   1.2487   0.04777   0.03772  -0.0654   0.0401   1.0000
   9.250   1.2456   0.05061   0.04071  -0.0633   0.0377   1.0000
   9.500   1.2399   0.05387   0.04410  -0.0616   0.0359   1.0000
   9.750   1.2377   0.05701   0.04742  -0.0602   0.0345   1.0000
  10.000   1.2382   0.06009   0.05078  -0.0590   0.0334   1.0000
  10.250   1.2389   0.06332   0.05427  -0.0579   0.0325   1.0000
  10.500   1.2395   0.06674   0.05796  -0.0570   0.0318   1.0000
  10.750   1.2390   0.07042   0.06191  -0.0564   0.0311   1.0000
  11.000   1.2367   0.07447   0.06623  -0.0562   0.0306   1.0000
  11.250   1.2318   0.07897   0.07102  -0.0566   0.0303   1.0000
  11.500   1.2240   0.08400   0.07631  -0.0576   0.0299   1.0000
  11.750   1.2138   0.08960   0.08216  -0.0594   0.0298   1.0000
  12.000   1.2013   0.09580   0.08861  -0.0619   0.0297   1.0000
  12.250   1.1871   0.10267   0.09572  -0.0652   0.0297   1.0000
  12.500   1.1713   0.11028   0.10356  -0.0693   0.0299   1.0000
  12.750   1.1542   0.11871   0.11219  -0.0741   0.0303   1.0000
  13.000   1.1364   0.12796   0.12163  -0.0797   0.0308   1.0000
<< Back to BE50 (original) (be50-il)

Polar data table (+)

Polar graphs


<< Back to BE50 (original) (be50-il)