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BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il)
Reynolds number: 200,000
Max Cl/Cd: 52.96 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-bacnlf-il-200000-n5.txt
Download as CSV file: xf-bacnlf-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5409   0.09366   0.09002  -0.0389   1.0014   0.0121
  -9.750  -0.5469   0.08891   0.08532  -0.0407   1.0014   0.0118
  -9.500  -0.5555   0.08347   0.07992  -0.0434   1.0014   0.0115
  -9.250  -0.5693   0.07753   0.07401  -0.0468   1.0014   0.0113
  -9.000  -0.5885   0.07308   0.06956  -0.0479   1.0014   0.0113
  -8.750  -0.6126   0.07005   0.06652  -0.0465   1.0014   0.0113
  -8.500  -0.6376   0.06776   0.06420  -0.0433   1.0014   0.0113
  -8.250  -0.6547   0.06467   0.06104  -0.0409   1.0014   0.0111
  -8.000  -0.6680   0.06134   0.05761  -0.0385   1.0014   0.0108
  -7.750  -0.6777   0.05765   0.05376  -0.0362   1.0014   0.0103
  -7.250  -0.6531   0.04461   0.03978  -0.0382   0.9958   0.0081
  -7.000  -0.6389   0.04046   0.03528  -0.0387   0.9930   0.0079
  -6.750  -0.6202   0.03654   0.03095  -0.0391   0.9904   0.0078
  -6.500  -0.5979   0.03291   0.02687  -0.0396   0.9882   0.0076
  -6.250  -0.5731   0.02966   0.02316  -0.0401   0.9867   0.0074
  -6.000  -0.5464   0.02683   0.01988  -0.0404   0.9855   0.0073
  -5.750  -0.5229   0.02455   0.01724  -0.0397   0.9833   0.0073
  -5.500  -0.4972   0.02259   0.01497  -0.0395   0.9813   0.0073
  -5.250  -0.4706   0.02093   0.01307  -0.0393   0.9795   0.0074
  -5.000  -0.4435   0.01952   0.01146  -0.0394   0.9779   0.0076
  -4.750  -0.4153   0.01833   0.01012  -0.0399   0.9762   0.0079
  -4.500  -0.3860   0.01725   0.00892  -0.0407   0.9747   0.0085
  -4.250  -0.3554   0.01639   0.00796  -0.0419   0.9734   0.0100
  -4.000  -0.3256   0.01571   0.00714  -0.0427   0.9717   0.0141
  -3.750  -0.2999   0.01514   0.00653  -0.0427   0.9686   0.0258
  -3.500  -0.2713   0.01448   0.00602  -0.0436   0.9662   0.0650
  -3.250  -0.2438   0.01209   0.00535  -0.0460   0.9654   0.4446
  -3.000  -0.2155   0.01184   0.00561  -0.0462   0.9634   0.6044
  -2.750  -0.1858   0.01209   0.00593  -0.0463   0.9614   0.6656
  -2.500  -0.1544   0.01229   0.00609  -0.0468   0.9599   0.6923
  -2.250  -0.1294   0.01232   0.00604  -0.0464   0.9563   0.6996
  -2.000  -0.1001   0.01231   0.00591  -0.0470   0.9534   0.7047
  -1.750  -0.0691   0.01228   0.00581  -0.0479   0.9510   0.7082
  -1.500  -0.0367   0.01226   0.00573  -0.0491   0.9492   0.7122
  -1.250  -0.0026   0.01225   0.00565  -0.0507   0.9476   0.7166
  -1.000   0.0248   0.01223   0.00560  -0.0508   0.9434   0.7203
  -0.750   0.0542   0.01220   0.00556  -0.0513   0.9395   0.7239
  -0.500   0.0869   0.01217   0.00551  -0.0526   0.9370   0.7279
  -0.250   0.1209   0.01216   0.00548  -0.0542   0.9351   0.7323
   0.000   0.1551   0.01212   0.00549  -0.0557   0.9337   0.7356
   0.250   0.1766   0.01218   0.00558  -0.0546   0.9278   0.7395
   0.500   0.2074   0.01218   0.00561  -0.0555   0.9246   0.7439
   0.750   0.2405   0.01214   0.00564  -0.0568   0.9224   0.7479
   1.000   0.2752   0.01207   0.00564  -0.0583   0.9204   0.7517
   1.250   0.2988   0.01208   0.00574  -0.0575   0.9131   0.7561
   1.500   0.3319   0.01196   0.00570  -0.0587   0.9091   0.7607
   1.750   0.3623   0.01180   0.00565  -0.0590   0.9026   0.7648
   2.000   0.3951   0.01150   0.00546  -0.0597   0.8945   0.7695
   2.250   0.4239   0.01093   0.00500  -0.0590   0.8737   0.7743
   2.500   0.4546   0.01032   0.00447  -0.0585   0.8408   0.7786
   2.750   0.4860   0.01005   0.00426  -0.0586   0.8093   0.7839
   3.000   0.5217   0.00985   0.00387  -0.0593   0.7179   0.7891
   3.250   0.5376   0.01069   0.00388  -0.0563   0.5368   0.7944
   3.500   0.5471   0.01193   0.00433  -0.0529   0.3629   0.8012
   3.750   0.5601   0.01311   0.00486  -0.0505   0.2084   0.8078
   4.250   0.5996   0.01458   0.00586  -0.0481   0.0793   0.8239
   4.500   0.6214   0.01511   0.00632  -0.0471   0.0534   0.8329
   4.750   0.6435   0.01559   0.00677  -0.0462   0.0336   0.8436
   5.000   0.6649   0.01614   0.00739  -0.0450   0.0213   0.8559
   5.250   0.6852   0.01686   0.00822  -0.0435   0.0156   0.8713
   5.500   0.7052   0.01752   0.00904  -0.0419   0.0135   0.8906
   5.750   0.7241   0.01846   0.01016  -0.0401   0.0123   0.9189
   6.000   0.7490   0.01962   0.01151  -0.0397   0.0117   0.9986
   6.250   0.7722   0.02096   0.01300  -0.0389   0.0113   0.9986
   6.500   0.7963   0.02240   0.01460  -0.0384   0.0107   0.9986
   6.750   0.8205   0.02354   0.01591  -0.0379   0.0095   0.9986
   7.000   0.8435   0.02462   0.01713  -0.0374   0.0085   0.9986
   7.500   0.8858   0.02864   0.02172  -0.0355   0.0079   0.9986
   7.750   0.9022   0.03167   0.02517  -0.0338   0.0077   0.9986
   8.000   0.9138   0.03521   0.02919  -0.0314   0.0076   0.9986
   8.250   0.9224   0.03870   0.03317  -0.0287   0.0075   0.9986
   8.500   0.9262   0.04253   0.03745  -0.0256   0.0075   0.9986
   8.750   0.9251   0.04660   0.04193  -0.0223   0.0076   0.9986
   9.250   0.9141   0.05454   0.05054  -0.0156   0.0077   0.9986
   9.500   0.9021   0.05851   0.05477  -0.0120   0.0077   0.9986
   9.750   0.8846   0.06370   0.06021  -0.0088   0.0079   0.9986
  10.000   0.8607   0.07005   0.06678  -0.0070   0.0082   0.9986
  10.250   0.8302   0.07843   0.07535  -0.0083   0.0085   0.9986
  10.500   0.8064   0.08731   0.08433  -0.0134   0.0087   0.9986
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