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BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il)
Reynolds number: 200,000
Max Cl/Cd: 55.77 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-bacnlf-il-200000.txt
Download as CSV file: xf-bacnlf-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5506   0.08704   0.08358  -0.0414   1.0014   0.0372
  -9.000  -0.5649   0.08171   0.07830  -0.0443   1.0014   0.0371
  -8.750  -0.5864   0.07741   0.07403  -0.0454   1.0014   0.0367
  -8.500  -0.6142   0.07456   0.07119  -0.0436   1.0014   0.0362
  -8.250  -0.6362   0.07173   0.06833  -0.0413   1.0014   0.0362
  -8.000  -0.6512   0.06865   0.06518  -0.0393   1.0014   0.0365
  -7.750  -0.6619   0.06550   0.06194  -0.0375   1.0014   0.0371
  -7.500  -0.6688   0.06228   0.05859  -0.0356   1.0014   0.0381
  -7.250  -0.6720   0.05904   0.05517  -0.0339   1.0014   0.0396
  -7.000  -0.6710   0.05903   0.05454  -0.0309   1.0014   0.0428
  -6.750  -0.6744   0.05341   0.04859  -0.0295   1.0014   0.0437
  -6.500  -0.6659   0.04825   0.04355  -0.0291   1.0014   0.0453
  -6.250  -0.6548   0.04544   0.04069  -0.0281   1.0014   0.0473
  -6.000  -0.6420   0.04290   0.03794  -0.0269   1.0014   0.0508
  -5.750  -0.6292   0.04000   0.03449  -0.0257   1.0014   0.0578
  -5.500  -0.6123   0.03716   0.03164  -0.0251   1.0014   0.0609
  -5.250  -0.5948   0.03498   0.02901  -0.0244   1.0014   0.0713
  -5.000  -0.5745   0.03265   0.02662  -0.0239   1.0014   0.0768
  -4.750  -0.5286   0.02499   0.01755  -0.0206   1.0014   0.0229
  -4.500  -0.5031   0.02442   0.01669  -0.0194   1.0014   0.0209
  -4.250  -0.4763   0.02202   0.01409  -0.0190   1.0014   0.0201
  -4.000  -0.4501   0.02027   0.01219  -0.0185   1.0014   0.0200
  -3.750  -0.4244   0.01899   0.01081  -0.0181   1.0014   0.0204
  -3.500  -0.3966   0.01706   0.00885  -0.0184   1.0014   0.0228
  -3.250  -0.3679   0.01587   0.00756  -0.0190   1.0014   0.0346
  -3.000  -0.3253   0.01237   0.00660  -0.0243   1.0014   0.5942
  -2.750  -0.3047   0.01279   0.00712  -0.0224   1.0014   0.6740
  -2.500  -0.2843   0.01316   0.00748  -0.0205   1.0014   0.7077
  -2.250  -0.2674   0.01362   0.00799  -0.0175   1.0014   0.7451
  -2.000  -0.2515   0.01399   0.00843  -0.0142   1.0014   0.7730
  -1.750  -0.2305   0.01413   0.00853  -0.0129   1.0014   0.7852
  -1.500  -0.2053   0.01416   0.00848  -0.0129   1.0014   0.7905
  -1.250  -0.1785   0.01423   0.00848  -0.0132   1.0008   0.7955
  -1.000  -0.1413   0.01438   0.00851  -0.0159   0.9979   0.8011
  -0.750  -0.1057   0.01453   0.00861  -0.0180   0.9952   0.8054
  -0.500  -0.0721   0.01465   0.00869  -0.0198   0.9913   0.8102
  -0.250  -0.0349   0.01483   0.00880  -0.0225   0.9881   0.8158
   0.000   0.0026   0.01504   0.00903  -0.0249   0.9854   0.8201
   0.250   0.0320   0.01509   0.00907  -0.0259   0.9797   0.8253
   0.500   0.0695   0.01524   0.00923  -0.0285   0.9756   0.8308
   0.750   0.1101   0.01545   0.00949  -0.0315   0.9725   0.8356
   1.000   0.1382   0.01547   0.00954  -0.0321   0.9653   0.8416
   1.250   0.1756   0.01559   0.00972  -0.0345   0.9614   0.8470
   1.500   0.2072   0.01567   0.00988  -0.0357   0.9554   0.8533
   1.750   0.2472   0.01566   0.00997  -0.0385   0.9491   0.8592
   2.000   0.2816   0.01556   0.00998  -0.0399   0.9403   0.8654
   2.250   0.3254   0.01544   0.00997  -0.0432   0.9347   0.8721
   2.500   0.3691   0.01483   0.00955  -0.0456   0.9218   0.8778
   2.750   0.4254   0.01341   0.00830  -0.0493   0.9024   0.8827
   3.000   0.4678   0.01251   0.00758  -0.0511   0.8903   0.8888
   3.250   0.5003   0.01155   0.00681  -0.0505   0.8705   0.8972
   3.500   0.5279   0.01079   0.00621  -0.0490   0.8457   0.9063
   3.750   0.5599   0.01004   0.00555  -0.0483   0.7944   0.9158
   4.000   0.5835   0.01051   0.00491  -0.0455   0.5374   0.9262
   4.250   0.5782   0.01273   0.00556  -0.0396   0.2234   0.9473
   4.500   0.5994   0.01437   0.00648  -0.0393   0.0953   0.9723
   4.750   0.6290   0.01519   0.00715  -0.0406   0.0596   0.9986
   5.000   0.6501   0.01663   0.00852  -0.0397   0.0344   0.9986
   5.250   0.6708   0.01864   0.01047  -0.0387   0.0281   0.9986
   5.500   0.6981   0.02007   0.01201  -0.0386   0.0265   0.9986
   5.750   0.7272   0.02202   0.01414  -0.0386   0.0256   0.9986
   6.000   0.7567   0.02444   0.01683  -0.0384   0.0253   0.9986
   6.250   0.7831   0.02652   0.01921  -0.0379   0.0239   0.9986
   6.500   0.8068   0.02857   0.02155  -0.0370   0.0224   0.9986
   6.750   0.8271   0.03273   0.02629  -0.0349   0.0238   0.9986
   7.000   0.8412   0.03733   0.03137  -0.0324   0.0260   0.9986
  11.000   0.6050   0.11012   0.10721  -0.0158   0.0441   0.9986
  11.250   0.6002   0.11450   0.11157  -0.0172   0.0433   0.9986
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