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BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il)
Reynolds number: 1,000,000
Max Cl/Cd: 66.14 at α=1°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-bacnlf-il-1000000-n5.txt
Download as CSV file: xf-bacnlf-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5435   0.13752   0.13578  -0.0204   1.0014   0.0051
 -12.500  -0.5406   0.13331   0.13158  -0.0220   1.0014   0.0051
  -7.750  -0.5727   0.02499   0.02133  -0.0699   0.9693   0.0030
  -7.500  -0.5517   0.02330   0.01942  -0.0695   0.9663   0.0030
  -7.250  -0.5342   0.01996   0.01569  -0.0686   0.9635   0.0028
  -7.000  -0.5130   0.01732   0.01269  -0.0680   0.9615   0.0027
  -6.500  -0.4666   0.01408   0.00900  -0.0669   0.9572   0.0026
  -6.250  -0.4429   0.01298   0.00775  -0.0664   0.9547   0.0026
  -6.000  -0.4186   0.01207   0.00671  -0.0661   0.9525   0.0026
  -5.750  -0.3937   0.01130   0.00583  -0.0659   0.9504   0.0025
  -5.500  -0.3680   0.01065   0.00507  -0.0658   0.9485   0.0025
  -5.250  -0.3415   0.01013   0.00446  -0.0658   0.9467   0.0025
  -5.000  -0.3153   0.00968   0.00395  -0.0658   0.9446   0.0025
  -4.750  -0.2886   0.00933   0.00353  -0.0658   0.9424   0.0025
  -4.500  -0.2615   0.00902   0.00317  -0.0659   0.9401   0.0025
  -4.250  -0.2342   0.00876   0.00285  -0.0660   0.9378   0.0025
  -4.000  -0.2064   0.00854   0.00259  -0.0662   0.9356   0.0026
  -3.750  -0.1784   0.00836   0.00237  -0.0664   0.9336   0.0026
  -3.500  -0.1508   0.00820   0.00219  -0.0666   0.9313   0.0028
  -3.250  -0.1231   0.00805   0.00202  -0.0668   0.9288   0.0035
  -3.000  -0.0954   0.00785   0.00186  -0.0670   0.9264   0.0143
  -2.750  -0.0678   0.00759   0.00171  -0.0672   0.9240   0.0424
  -2.500  -0.0412   0.00698   0.00149  -0.0676   0.9216   0.1618
  -2.250  -0.0161   0.00587   0.00117  -0.0681   0.9188   0.3941
  -2.000   0.0094   0.00514   0.00112  -0.0682   0.9152   0.5891
  -1.750   0.0374   0.00508   0.00113  -0.0684   0.9119   0.6181
  -1.500   0.0659   0.00505   0.00112  -0.0686   0.9091   0.6293
  -1.250   0.0947   0.00504   0.00107  -0.0689   0.9065   0.6340
  -1.000   0.1231   0.00502   0.00106  -0.0692   0.9034   0.6373
  -0.750   0.1516   0.00500   0.00106  -0.0695   0.8999   0.6406
  -0.500   0.1801   0.00499   0.00104  -0.0697   0.8962   0.6440
  -0.250   0.2086   0.00497   0.00101  -0.0699   0.8913   0.6472
   0.000   0.2365   0.00495   0.00099  -0.0700   0.8829   0.6502
   0.250   0.2645   0.00493   0.00097  -0.0701   0.8738   0.6532
   0.500   0.2924   0.00492   0.00095  -0.0702   0.8633   0.6563
   0.750   0.3192   0.00496   0.00092  -0.0699   0.8383   0.6594
   1.000   0.3426   0.00518   0.00088  -0.0688   0.7718   0.6625
   1.250   0.3636   0.00561   0.00096  -0.0674   0.6818   0.6654
   1.500   0.3870   0.00595   0.00108  -0.0666   0.6198   0.6684
   1.750   0.4051   0.00676   0.00132  -0.0649   0.4752   0.6715
   2.000   0.4254   0.00749   0.00157  -0.0637   0.3477   0.6746
   2.250   0.4453   0.00831   0.00183  -0.0626   0.2039   0.6776
   2.500   0.4678   0.00891   0.00207  -0.0618   0.1081   0.6806
   2.750   0.4933   0.00920   0.00225  -0.0616   0.0747   0.6838
   3.000   0.5191   0.00946   0.00243  -0.0614   0.0518   0.6870
   3.250   0.5452   0.00969   0.00261  -0.0612   0.0370   0.6900
   3.500   0.5710   0.00995   0.00281  -0.0610   0.0223   0.6931
   3.750   0.5961   0.01028   0.00307  -0.0606   0.0075   0.6964
   4.000   0.6220   0.01053   0.00335  -0.0603   0.0054   0.6999
   4.250   0.6480   0.01078   0.00363  -0.0601   0.0045   0.7031
   4.500   0.6739   0.01101   0.00391  -0.0599   0.0042   0.7062
   4.750   0.6994   0.01128   0.00424  -0.0596   0.0041   0.7097
   5.000   0.7248   0.01158   0.00459  -0.0592   0.0039   0.7136
   5.250   0.7499   0.01191   0.00500  -0.0588   0.0037   0.7173
   5.500   0.7747   0.01228   0.00542  -0.0584   0.0035   0.7207
   5.750   0.7992   0.01267   0.00589  -0.0579   0.0033   0.7246
   6.000   0.8233   0.01313   0.00642  -0.0573   0.0031   0.7287
   6.250   0.8462   0.01376   0.00713  -0.0565   0.0028   0.7330
   6.500   0.8663   0.01486   0.00841  -0.0551   0.0026   0.7379
   6.750   0.8892   0.01555   0.00923  -0.0543   0.0025   0.7432
   7.000   0.9121   0.01624   0.01005  -0.0535   0.0024   0.7484
   7.250   0.9343   0.01709   0.01105  -0.0526   0.0024   0.7549
   7.500   0.9561   0.01804   0.01216  -0.0516   0.0024   0.7621
   7.750   0.9773   0.01915   0.01348  -0.0505   0.0023   0.7709
   8.000   0.9974   0.02048   0.01504  -0.0493   0.0023   0.7810
   8.250   1.0164   0.02200   0.01683  -0.0479   0.0023   0.7930
   8.500   1.0334   0.02380   0.01894  -0.0462   0.0023   0.8079
   8.750   1.0476   0.02598   0.02150  -0.0440   0.0023   0.8275
   9.000   1.0574   0.02861   0.02459  -0.0412   0.0023   0.8539
   9.250   1.0603   0.03188   0.02839  -0.0373   0.0023   0.8949
   9.500   1.0537   0.03615   0.03325  -0.0322   0.0023   0.9986
   9.750   1.0259   0.04479   0.04250  -0.0253   0.0024   0.9986
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