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BE50 (original) (be50-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: BE50 (original) (be50-il)
Reynolds number: 100,000
Max Cl/Cd: 59.69 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-be50-il-100000.txt
Download as CSV file: xf-be50-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3677   0.09510   0.09029  -0.0205   1.0000   0.0823
  -8.000  -0.3729   0.09346   0.08875  -0.0227   1.0000   0.0851
  -7.750  -0.3750   0.09229   0.08768  -0.0336   1.0000   0.0865
  -7.500  -0.3700   0.08713   0.08258  -0.0286   1.0000   0.0880
  -7.250  -0.3615   0.08385   0.07933  -0.0243   1.0000   0.0909
  -7.000  -0.3558   0.08113   0.07664  -0.0247   1.0000   0.0947
  -6.750  -0.3393   0.07793   0.07339  -0.0436   1.0000   0.1009
  -6.500  -0.3422   0.07448   0.07008  -0.0319   1.0000   0.1033
  -6.250  -0.3345   0.07200   0.06763  -0.0301   1.0000   0.1090
  -6.000  -0.3154   0.06754   0.06311  -0.0400   1.0000   0.1163
  -5.750  -0.3096   0.06506   0.06069  -0.0360   1.0000   0.1196
  -5.500  -0.2827   0.06059   0.05608  -0.0454   1.0000   0.1305
  -5.250  -0.2761   0.05824   0.05379  -0.0416   1.0000   0.1341
  -5.000  -0.2499   0.05423   0.04966  -0.0478   1.0000   0.1459
  -4.750  -0.2274   0.05111   0.04645  -0.0509   1.0000   0.1599
  -4.500  -0.2074   0.04838   0.04366  -0.0523   1.0000   0.1746
  -4.250  -0.1853   0.04564   0.04084  -0.0541   1.0000   0.1892
  -4.000  -0.1639   0.04311   0.03826  -0.0552   1.0000   0.2042
  -3.750  -0.0652   0.02966   0.02291  -0.0739   1.0000   0.0988
  -3.500  -0.0327   0.02692   0.01977  -0.0757   1.0000   0.0968
  -3.250   0.0043   0.02409   0.01632  -0.0778   1.0000   0.0911
  -3.000   0.0391   0.02224   0.01386  -0.0790   1.0000   0.0885
  -2.750   0.0692   0.02102   0.01240  -0.0797   1.0000   0.0893
  -2.500   0.0974   0.02018   0.01143  -0.0802   1.0000   0.0922
  -2.250   0.1237   0.01977   0.01090  -0.0805   1.0000   0.0991
  -2.000   0.1517   0.01913   0.01029  -0.0811   1.0000   0.1051
  -1.750   0.2022   0.01830   0.00955  -0.0856   0.9940   0.1211
  -1.500   0.2554   0.01644   0.00882  -0.0909   0.9884   0.3479
  -1.250   0.2922   0.01477   0.00868  -0.0918   0.9778   1.0000
  -1.000   0.3431   0.01490   0.00844  -0.0964   0.9653   1.0000
  -0.750   0.3917   0.01496   0.00824  -0.1004   0.9535   1.0000
  -0.500   0.4380   0.01495   0.00806  -0.1040   0.9418   1.0000
  -0.250   0.4807   0.01489   0.00787  -0.1066   0.9286   1.0000
   0.000   0.5206   0.01477   0.00766  -0.1086   0.9150   1.0000
   0.250   0.5583   0.01459   0.00741  -0.1099   0.9008   1.0000
   0.500   0.5941   0.01437   0.00714  -0.1106   0.8859   1.0000
   0.750   0.6282   0.01412   0.00684  -0.1109   0.8703   1.0000
   1.000   0.6571   0.01397   0.00665  -0.1102   0.8504   1.0000
   1.250   0.6873   0.01376   0.00640  -0.1096   0.8309   1.0000
   1.500   0.7156   0.01363   0.00624  -0.1086   0.8089   1.0000
   1.750   0.7434   0.01355   0.00607  -0.1075   0.7852   1.0000
   2.000   0.7694   0.01359   0.00602  -0.1062   0.7575   1.0000
   2.250   0.7950   0.01372   0.00605  -0.1048   0.7276   1.0000
   2.500   0.8197   0.01393   0.00615  -0.1034   0.6940   1.0000
   2.750   0.8443   0.01421   0.00629  -0.1021   0.6582   1.0000
   3.000   0.8686   0.01456   0.00648  -0.1008   0.6211   1.0000
   3.250   0.8930   0.01496   0.00675  -0.0997   0.5853   1.0000
   3.500   0.9176   0.01542   0.00703  -0.0988   0.5533   1.0000
   3.750   0.9424   0.01593   0.00740  -0.0980   0.5248   1.0000
   4.000   0.9674   0.01646   0.00786  -0.0973   0.4985   1.0000
   4.250   0.9924   0.01700   0.00839  -0.0967   0.4751   1.0000
   4.500   1.0175   0.01752   0.00886  -0.0961   0.4543   1.0000
   4.750   1.0425   0.01808   0.00941  -0.0955   0.4345   1.0000
   5.000   1.0675   0.01870   0.01002  -0.0949   0.4157   1.0000
   5.250   1.0926   0.01943   0.01073  -0.0944   0.3982   1.0000
   5.500   1.1179   0.02027   0.01152  -0.0939   0.3815   1.0000
   5.750   1.1413   0.02099   0.01236  -0.0931   0.3614   1.0000
   6.000   1.1640   0.02163   0.01295  -0.0923   0.3396   1.0000
   6.250   1.1840   0.02198   0.01339  -0.0910   0.3134   1.0000
   6.500   1.2022   0.02204   0.01356  -0.0895   0.2829   1.0000
   6.750   1.2223   0.02220   0.01393  -0.0883   0.2554   1.0000
   7.000   1.2408   0.02239   0.01422  -0.0869   0.2047   1.0000
   7.250   1.2426   0.02578   0.01640  -0.0836   0.0720   1.0000
   7.500   1.2536   0.02801   0.01860  -0.0812   0.0580   1.0000
   7.750   1.2631   0.03016   0.02081  -0.0786   0.0526   1.0000
   8.000   1.2757   0.03200   0.02279  -0.0762   0.0490   1.0000
   8.250   1.2880   0.03398   0.02484  -0.0741   0.0458   1.0000
   8.500   1.3011   0.03684   0.02762  -0.0723   0.0428   1.0000
   8.750   1.3193   0.03882   0.02985  -0.0707   0.0408   1.0000
   9.000   1.3391   0.04144   0.03268  -0.0694   0.0397   1.0000
   9.250   1.3575   0.04441   0.03593  -0.0680   0.0391   1.0000
   9.500   1.3722   0.04771   0.03958  -0.0664   0.0389   1.0000
   9.750   1.3814   0.05129   0.04356  -0.0642   0.0390   1.0000
  10.000   1.3843   0.05507   0.04781  -0.0617   0.0393   1.0000
  10.250   1.3813   0.05897   0.05213  -0.0590   0.0397   1.0000
  10.500   1.3720   0.06272   0.05624  -0.0558   0.0401   1.0000
  10.750   1.3577   0.06638   0.06020  -0.0527   0.0404   1.0000
  11.000   1.3406   0.07030   0.06441  -0.0504   0.0406   1.0000
  11.250   1.3219   0.07468   0.06904  -0.0490   0.0409   1.0000
  11.500   1.3018   0.07958   0.07418  -0.0489   0.0412   1.0000
  11.750   1.2806   0.08510   0.07993  -0.0499   0.0415   1.0000
  12.000   1.2587   0.09131   0.08633  -0.0521   0.0418   1.0000
  12.250   1.2372   0.09820   0.09338  -0.0552   0.0422   1.0000
  12.500   1.2172   0.10566   0.10092  -0.0587   0.0427   1.0000
  12.750   1.2017   0.11290   0.10831  -0.0623   0.0433   1.0000
  13.000   1.1693   0.12352   0.11916  -0.0721   0.0442   1.0000
  13.250   0.9819   0.11535   0.11108  -0.0499   0.0433   1.0000
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