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BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il)
Reynolds number: 500,000
Max Cl/Cd: 78.38 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-bacnlf-il-500000.txt
Download as CSV file: xf-bacnlf-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.4327   0.17446   0.17220  -0.0170   1.0014   0.0083
 -17.000  -0.4273   0.17033   0.16807  -0.0171   1.0014   0.0087
  -5.250  -0.4503   0.02070   0.01495  -0.0461   0.9775   0.0119
  -5.000  -0.4210   0.01729   0.01107  -0.0454   0.9769   0.0087
  -4.750  -0.3894   0.01651   0.01020  -0.0463   0.9758   0.0084
  -4.500  -0.3591   0.01511   0.00871  -0.0471   0.9749   0.0082
  -4.250  -0.3276   0.01396   0.00746  -0.0483   0.9740   0.0082
  -4.000  -0.2953   0.01295   0.00632  -0.0497   0.9732   0.0086
  -3.750  -0.2613   0.01227   0.00553  -0.0514   0.9725   0.0104
  -3.500  -0.2399   0.01171   0.00496  -0.0502   0.9682   0.0283
  -3.250  -0.2102   0.01061   0.00454  -0.0518   0.9666   0.1925
  -3.000  -0.1787   0.00901   0.00413  -0.0543   0.9662   0.5166
  -2.750  -0.1470   0.00885   0.00416  -0.0554   0.9645   0.5912
  -2.500  -0.1142   0.00887   0.00424  -0.0566   0.9630   0.6341
  -2.250  -0.0811   0.00908   0.00453  -0.0575   0.9615   0.6770
  -2.000  -0.0464   0.00919   0.00468  -0.0589   0.9603   0.6952
  -1.750  -0.0201   0.00921   0.00467  -0.0587   0.9561   0.7022
  -1.500   0.0112   0.00916   0.00458  -0.0596   0.9532   0.7060
  -1.250   0.0444   0.00911   0.00453  -0.0610   0.9515   0.7094
  -1.000   0.0785   0.00907   0.00448  -0.0626   0.9501   0.7132
  -0.750   0.1138   0.00903   0.00442  -0.0644   0.9491   0.7171
  -0.500   0.1489   0.00896   0.00436  -0.0662   0.9481   0.7203
  -0.250   0.1835   0.00889   0.00432  -0.0678   0.9471   0.7236
   0.000   0.2060   0.00893   0.00438  -0.0668   0.9415   0.7275
   0.250   0.2387   0.00883   0.00430  -0.0680   0.9387   0.7314
   0.500   0.2739   0.00863   0.00414  -0.0695   0.9364   0.7345
   0.750   0.3104   0.00838   0.00395  -0.0712   0.9342   0.7381
   1.000   0.3358   0.00827   0.00388  -0.0706   0.9270   0.7422
   1.250   0.3715   0.00782   0.00345  -0.0717   0.9206   0.7459
   1.500   0.3983   0.00729   0.00296  -0.0706   0.9049   0.7494
   1.750   0.4249   0.00707   0.00278  -0.0701   0.8934   0.7535
   2.000   0.4512   0.00692   0.00271  -0.0695   0.8807   0.7580
   2.250   0.4772   0.00677   0.00259  -0.0688   0.8604   0.7620
   2.500   0.5040   0.00666   0.00251  -0.0683   0.8350   0.7661
   2.750   0.5283   0.00674   0.00239  -0.0671   0.7645   0.7708
   3.000   0.5356   0.00790   0.00255  -0.0626   0.5481   0.7758
   3.250   0.5460   0.00921   0.00301  -0.0595   0.3461   0.7808
   3.500   0.5630   0.01025   0.00342  -0.0579   0.1934   0.7865
   3.750   0.5833   0.01100   0.00379  -0.0569   0.1028   0.7917
   4.000   0.6066   0.01147   0.00412  -0.0562   0.0634   0.7979
   4.250   0.6306   0.01186   0.00447  -0.0557   0.0404   0.8044
   4.500   0.6529   0.01251   0.00508  -0.0545   0.0169   0.8115
   4.750   0.6765   0.01301   0.00565  -0.0537   0.0139   0.8190
   5.000   0.6977   0.01381   0.00659  -0.0524   0.0119   0.8279
   5.250   0.7205   0.01432   0.00723  -0.0514   0.0111   0.8378
   5.500   0.7419   0.01505   0.00812  -0.0501   0.0105   0.8499
   5.750   0.7628   0.01587   0.00910  -0.0487   0.0100   0.8652
   6.250   0.8008   0.01774   0.01138  -0.0448   0.0091   0.9196
   6.500   0.8258   0.01939   0.01330  -0.0441   0.0090   0.9986
   6.750   0.8502   0.02268   0.01699  -0.0429   0.0096   0.9986
   7.000   0.8671   0.02792   0.02284  -0.0403   0.0110   0.9986
   7.750   0.8694   0.04962   0.04601  -0.0282   0.0188   0.9986
   8.000   0.8724   0.05316   0.04982  -0.0254   0.0187   0.9986
   8.250   0.8730   0.05667   0.05359  -0.0225   0.0187   0.9986
   8.500   0.8713   0.06011   0.05726  -0.0197   0.0186   0.9986
   8.750   0.8691   0.06323   0.06060  -0.0169   0.0184   0.9986
   9.000   0.8753   0.06593   0.06356  -0.0147   0.0173   0.9986
   9.250   0.8626   0.06983   0.06761  -0.0119   0.0169   0.9986
   9.500   0.8453   0.07388   0.07176  -0.0099   0.0168   0.9986
   9.750   0.8262   0.07854   0.07650  -0.0096   0.0168   0.9986
  10.000   0.8067   0.08426   0.08231  -0.0116   0.0170   0.9986
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