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BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.34 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-bacnlf-il-1000000.txt
Download as CSV file: xf-bacnlf-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5568   0.07979   0.07822  -0.0431   1.0014   0.0082
  -9.250  -0.5775   0.07503   0.07346  -0.0439   1.0014   0.0082
  -9.000  -0.5914   0.06932   0.06769  -0.0481   1.0003   0.0082
  -8.750  -0.5985   0.06347   0.06172  -0.0544   0.9975   0.0082
  -8.500  -0.5948   0.05796   0.05604  -0.0586   0.9949   0.0082
  -8.250  -0.5895   0.05320   0.05109  -0.0607   0.9917   0.0082
  -8.000  -0.5795   0.04853   0.04620  -0.0626   0.9894   0.0083
  -7.750  -0.5655   0.04405   0.04147  -0.0643   0.9878   0.0083
  -7.500  -0.5480   0.03983   0.03696  -0.0660   0.9866   0.0083
  -5.500  -0.3652   0.01312   0.00787  -0.0678   0.9741   0.0054
  -5.250  -0.3345   0.01257   0.00726  -0.0687   0.9734   0.0052
  -5.000  -0.3079   0.01131   0.00590  -0.0689   0.9719   0.0050
  -4.750  -0.2865   0.01052   0.00501  -0.0679   0.9682   0.0049
  -4.500  -0.2590   0.00989   0.00428  -0.0681   0.9660   0.0049
  -4.250  -0.2300   0.00942   0.00372  -0.0685   0.9643   0.0049
  -4.000  -0.2004   0.00907   0.00331  -0.0691   0.9628   0.0051
  -3.750  -0.1704   0.00877   0.00295  -0.0698   0.9615   0.0068
  -3.500  -0.1408   0.00846   0.00270  -0.0704   0.9603   0.0236
  -3.250  -0.1147   0.00804   0.00248  -0.0705   0.9579   0.0810
  -3.000  -0.0896   0.00743   0.00224  -0.0705   0.9550   0.1925
  -2.750  -0.0650   0.00623   0.00188  -0.0709   0.9525   0.4289
  -2.500  -0.0378   0.00567   0.00179  -0.0713   0.9504   0.5728
  -2.250  -0.0087   0.00556   0.00176  -0.0716   0.9485   0.6087
  -2.000   0.0194   0.00557   0.00185  -0.0717   0.9463   0.6453
  -1.750   0.0462   0.00560   0.00190  -0.0715   0.9429   0.6582
  -1.500   0.0742   0.00559   0.00189  -0.0716   0.9401   0.6659
  -1.250   0.1029   0.00556   0.00185  -0.0718   0.9377   0.6699
  -1.000   0.1319   0.00554   0.00181  -0.0722   0.9355   0.6735
  -0.750   0.1607   0.00555   0.00180  -0.0725   0.9333   0.6767
  -0.500   0.1878   0.00550   0.00179  -0.0724   0.9295   0.6800
  -0.250   0.2155   0.00545   0.00175  -0.0724   0.9250   0.6831
   0.000   0.2438   0.00538   0.00167  -0.0725   0.9207   0.6864
   0.250   0.2709   0.00535   0.00164  -0.0723   0.9147   0.6897
   0.500   0.2987   0.00526   0.00156  -0.0723   0.9088   0.6928
   0.750   0.3251   0.00514   0.00147  -0.0718   0.8978   0.6959
   1.000   0.3514   0.00503   0.00132  -0.0713   0.8800   0.6991
   1.250   0.3788   0.00502   0.00130  -0.0712   0.8670   0.7025
   1.500   0.4065   0.00501   0.00130  -0.0712   0.8544   0.7058
   1.750   0.4327   0.00503   0.00127  -0.0707   0.8259   0.7089
   2.000   0.4576   0.00518   0.00130  -0.0700   0.7813   0.7122
   2.250   0.4709   0.00606   0.00146  -0.0669   0.6108   0.7159
   2.500   0.4852   0.00716   0.00179  -0.0645   0.4197   0.7193
   2.750   0.5042   0.00798   0.00208  -0.0632   0.2796   0.7229
   3.000   0.5249   0.00872   0.00237  -0.0621   0.1622   0.7265
   3.250   0.5484   0.00922   0.00262  -0.0615   0.0975   0.7303
   3.500   0.5728   0.00960   0.00284  -0.0611   0.0577   0.7340
   3.750   0.5981   0.00989   0.00307  -0.0608   0.0365   0.7381
   4.000   0.6224   0.01032   0.00338  -0.0602   0.0120   0.7425
   4.250   0.6477   0.01065   0.00372  -0.0598   0.0080   0.7467
   4.500   0.6731   0.01094   0.00410  -0.0594   0.0074   0.7512
   4.750   0.6983   0.01127   0.00450  -0.0590   0.0071   0.7562
   5.000   0.7232   0.01164   0.00495  -0.0585   0.0067   0.7615
   5.250   0.7475   0.01206   0.00548  -0.0578   0.0062   0.7673
   5.500   0.7715   0.01255   0.00604  -0.0572   0.0057   0.7737
   5.750   0.7944   0.01317   0.00677  -0.0563   0.0053   0.7807
   6.250   0.8367   0.01512   0.00903  -0.0537   0.0049   0.7984
   6.500   0.8587   0.01614   0.01022  -0.0526   0.0050   0.8099
   6.750   0.8808   0.01733   0.01162  -0.0514   0.0051   0.8243
   7.250   0.8901   0.03422   0.03043  -0.0401   0.0116   0.8601
   7.500   0.8637   0.02349   0.02008  -0.0318   0.0108   0.8419
   7.750   0.8714   0.02665   0.02359  -0.0286   0.0102   0.8668
   8.000   0.8729   0.02997   0.02727  -0.0247   0.0097   0.9108
   8.250   0.8734   0.03369   0.03129  -0.0211   0.0093   0.9986
   8.500   0.8717   0.03767   0.03545  -0.0179   0.0091   0.9986
   8.750   0.8663   0.04165   0.03961  -0.0146   0.0089   0.9986
   9.000   0.8571   0.04550   0.04360  -0.0111   0.0088   0.9986
   9.250   0.8394   0.04899   0.04722  -0.0067   0.0087   0.9986
   9.500   0.8170   0.05267   0.05102  -0.0027   0.0087   0.9986
   9.750   0.7898   0.05721   0.05567   0.0001   0.0087   0.9986
  10.000   0.7593   0.06271   0.06129   0.0011   0.0088   0.9986
  10.250   0.7226   0.07046   0.06914  -0.0007   0.0091   0.9986
  10.500   0.6803   0.08393   0.08268  -0.0099   0.0096   0.9986
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