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BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il)
Reynolds number: 500,000
Max Cl/Cd: 64.91 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-bacnlf-il-500000-n5.txt
Download as CSV file: xf-bacnlf-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING HSNLF AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6078   0.04687   0.04385  -0.0625   0.9871   0.0050
  -8.000  -0.5990   0.04193   0.03859  -0.0641   0.9849   0.0048
  -7.750  -0.5909   0.03778   0.03415  -0.0635   0.9805   0.0046
  -7.500  -0.5754   0.03341   0.02941  -0.0637   0.9777   0.0044
  -7.250  -0.5561   0.02903   0.02461  -0.0639   0.9758   0.0042
  -7.000  -0.5338   0.02480   0.01990  -0.0639   0.9744   0.0040
  -6.750  -0.5092   0.02094   0.01553  -0.0638   0.9734   0.0038
  -6.500  -0.4827   0.01825   0.01244  -0.0638   0.9725   0.0036
  -6.250  -0.4627   0.01668   0.01065  -0.0624   0.9690   0.0035
  -6.000  -0.4385   0.01539   0.00917  -0.0620   0.9668   0.0035
  -5.750  -0.4125   0.01434   0.00799  -0.0621   0.9649   0.0035
  -5.500  -0.3852   0.01348   0.00699  -0.0624   0.9634   0.0035
  -5.250  -0.3569   0.01276   0.00617  -0.0630   0.9620   0.0035
  -5.000  -0.3279   0.01217   0.00548  -0.0637   0.9608   0.0036
  -4.750  -0.2983   0.01168   0.00492  -0.0644   0.9598   0.0038
  -4.500  -0.2736   0.01134   0.00450  -0.0640   0.9569   0.0040
  -4.250  -0.2467   0.01102   0.00410  -0.0641   0.9544   0.0043
  -4.000  -0.2184   0.01072   0.00375  -0.0644   0.9524   0.0053
  -3.750  -0.1894   0.01041   0.00345  -0.0650   0.9506   0.0129
  -3.500  -0.1599   0.01008   0.00318  -0.0657   0.9491   0.0298
  -3.250  -0.1303   0.00972   0.00290  -0.0664   0.9477   0.0652
  -3.000  -0.1039   0.00904   0.00263  -0.0668   0.9455   0.1766
  -2.750  -0.0826   0.00753   0.00223  -0.0670   0.9420   0.4718
  -2.500  -0.0566   0.00717   0.00236  -0.0669   0.9395   0.6119
  -2.250  -0.0278   0.00718   0.00241  -0.0671   0.9375   0.6420
  -2.000   0.0018   0.00717   0.00238  -0.0676   0.9358   0.6524
  -1.750   0.0319   0.00713   0.00231  -0.0682   0.9342   0.6564
  -1.500   0.0594   0.00713   0.00227  -0.0682   0.9310   0.6603
  -1.250   0.0867   0.00711   0.00223  -0.0682   0.9270   0.6637
  -1.000   0.1155   0.00706   0.00218  -0.0685   0.9238   0.6668
  -0.750   0.1450   0.00702   0.00213  -0.0689   0.9214   0.6700
  -0.500   0.1742   0.00700   0.00211  -0.0693   0.9192   0.6736
  -0.250   0.2008   0.00702   0.00214  -0.0692   0.9151   0.6770
   0.000   0.2288   0.00699   0.00215  -0.0694   0.9117   0.6797
   0.250   0.2577   0.00696   0.00213  -0.0697   0.9085   0.6828
   0.500   0.2856   0.00691   0.00212  -0.0697   0.9035   0.6864
   0.750   0.3129   0.00685   0.00207  -0.0696   0.8957   0.6898
   1.000   0.3402   0.00678   0.00204  -0.0694   0.8871   0.6926
   1.250   0.3672   0.00666   0.00194  -0.0690   0.8710   0.6957
   1.500   0.3936   0.00655   0.00173  -0.0683   0.8306   0.6992
   1.750   0.4200   0.00662   0.00166  -0.0678   0.7879   0.7028
   2.000   0.4440   0.00684   0.00169  -0.0668   0.7281   0.7059
   2.250   0.4586   0.00762   0.00187  -0.0640   0.5880   0.7090
   2.500   0.4741   0.00852   0.00218  -0.0618   0.4408   0.7126
   2.750   0.4919   0.00944   0.00251  -0.0603   0.3003   0.7165
   3.000   0.5097   0.01046   0.00290  -0.0588   0.1460   0.7200
   3.250   0.5327   0.01098   0.00318  -0.0582   0.0842   0.7235
   3.500   0.5577   0.01128   0.00343  -0.0579   0.0620   0.7273
   3.750   0.5830   0.01159   0.00368  -0.0575   0.0444   0.7315
   4.000   0.6078   0.01190   0.00397  -0.0571   0.0297   0.7355
   4.250   0.6325   0.01224   0.00430  -0.0567   0.0164   0.7400
   4.500   0.6569   0.01265   0.00470  -0.0562   0.0089   0.7446
   4.750   0.6814   0.01304   0.00516  -0.0556   0.0075   0.7490
   5.000   0.7060   0.01340   0.00563  -0.0550   0.0069   0.7542
   5.500   0.7541   0.01423   0.00666  -0.0539   0.0055   0.7661
   5.750   0.7775   0.01477   0.00730  -0.0531   0.0052   0.7730
   6.000   0.7996   0.01547   0.00813  -0.0522   0.0048   0.7803
   6.250   0.8206   0.01639   0.00920  -0.0510   0.0046   0.7890
   6.500   0.8428   0.01712   0.01009  -0.0500   0.0044   0.7993
   6.750   0.8645   0.01798   0.01112  -0.0489   0.0043   0.8110
   7.000   0.8857   0.01898   0.01235  -0.0478   0.0041   0.8248
   7.250   0.9063   0.02016   0.01378  -0.0464   0.0040   0.8415
   7.500   0.9258   0.02151   0.01544  -0.0449   0.0039   0.8637
   7.750   0.9427   0.02307   0.01735  -0.0427   0.0038   0.8972
   8.000   0.9599   0.02504   0.01975  -0.0407   0.0038   0.9986
   8.250   0.9752   0.02779   0.02291  -0.0387   0.0038   0.9986
   8.500   0.9850   0.03140   0.02701  -0.0358   0.0038   0.9986
   8.750   0.9860   0.03634   0.03251  -0.0318   0.0039   0.9986
   9.000   0.9766   0.04276   0.03947  -0.0268   0.0040   0.9986
   9.250   0.9615   0.04971   0.04683  -0.0219   0.0041   0.9986
   9.500   0.9462   0.05550   0.05290  -0.0178   0.0042   0.9986
   9.750   0.9274   0.06011   0.05771  -0.0138   0.0042   0.9986
  10.000   0.9062   0.06472   0.06248  -0.0107   0.0043   0.9986
  10.250   0.8847   0.06970   0.06759  -0.0094   0.0043   0.9986
  10.500   0.8616   0.07578   0.07380  -0.0104   0.0043   0.9986
  10.750   0.8394   0.08379   0.08191  -0.0151   0.0043   0.9986
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