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NACA 16-006 (naca16006-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 16-006 (naca16006-il)
Reynolds number: 50,000
Max Cl/Cd: 16.38 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16006-il-50000-n5.txt
Download as CSV file: xf-naca16006-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-006                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6498   0.13489   0.12779   0.0097   1.0000   0.0825
 -10.500  -0.6576   0.13241   0.12540   0.0054   1.0000   0.0849
 -10.250  -0.6652   0.12962   0.12270   0.0012   1.0000   0.0855
 -10.000  -0.6467   0.12301   0.11605   0.0050   1.0000   0.0889
  -9.750  -0.6429   0.11904   0.11210   0.0044   1.0000   0.0920
  -9.500  -0.6440   0.11536   0.10847   0.0023   1.0000   0.0957
  -9.250  -0.6609   0.11278   0.10604  -0.0046   1.0000   0.0990
  -9.000  -0.6527   0.10745   0.10074  -0.0034   1.0000   0.1011
  -8.750  -0.6455   0.10320   0.09649  -0.0026   1.0000   0.1049
  -8.500  -0.6481   0.09926   0.09261  -0.0050   1.0000   0.1086
  -8.000  -0.5530   0.07522   0.06887  -0.0205   1.0000   0.0557
  -7.750  -0.5604   0.07088   0.06456  -0.0205   1.0000   0.0525
  -7.500  -0.6466   0.07930   0.07250  -0.0158   1.0000   0.0557
  -7.250  -0.6417   0.07425   0.06727  -0.0168   1.0000   0.0437
  -7.000  -0.6378   0.06993   0.06287  -0.0166   1.0000   0.0413
  -6.750  -0.6313   0.06558   0.05803  -0.0167   1.0000   0.0355
  -6.500  -0.6239   0.06142   0.05376  -0.0157   1.0000   0.0349
  -6.250  -0.6155   0.05754   0.04966  -0.0145   1.0000   0.0346
  -6.000  -0.6056   0.05381   0.04564  -0.0131   1.0000   0.0344
  -5.750  -0.5941   0.05019   0.04169  -0.0115   1.0000   0.0343
  -5.500  -0.5811   0.04670   0.03782  -0.0097   1.0000   0.0340
  -5.250  -0.5664   0.04331   0.03396  -0.0079   1.0000   0.0335
  -5.000  -0.5498   0.04005   0.03027  -0.0059   1.0000   0.0329
  -4.750  -0.5311   0.03698   0.02670  -0.0040   1.0000   0.0325
  -4.500  -0.5101   0.03409   0.02330  -0.0022   1.0000   0.0325
  -4.250  -0.4868   0.03146   0.02015  -0.0006   1.0000   0.0336
  -4.000  -0.4620   0.02909   0.01728   0.0008   1.0000   0.0368
  -3.750  -0.4362   0.02685   0.01483   0.0017   1.0000   0.0406
  -3.500  -0.4070   0.02489   0.01252   0.0027   1.0000   0.0447
  -3.250  -0.3795   0.02318   0.01055   0.0033   1.0000   0.0564
  -3.000  -0.2118   0.01747   0.00757  -0.0197   1.0000   1.0000
  -2.750  -0.1931   0.01721   0.00682  -0.0183   1.0000   1.0000
  -2.500  -0.1746   0.01699   0.00625  -0.0169   1.0000   1.0000
  -2.250  -0.1563   0.01679   0.00577  -0.0155   1.0000   1.0000
  -2.000  -0.1383   0.01663   0.00535  -0.0140   1.0000   1.0000
  -1.750  -0.1205   0.01649   0.00494  -0.0124   1.0000   1.0000
  -1.500  -0.1029   0.01637   0.00465  -0.0107   1.0000   1.0000
  -1.250  -0.0856   0.01627   0.00442  -0.0090   1.0000   1.0000
  -1.000  -0.0684   0.01619   0.00423  -0.0072   1.0000   1.0000
  -0.750  -0.0513   0.01613   0.00409  -0.0054   1.0000   1.0000
  -0.500  -0.0341   0.01609   0.00397  -0.0036   1.0000   1.0000
  -0.250  -0.0171   0.01606   0.00391  -0.0018   1.0000   1.0000
   0.000   0.0000   0.01605   0.00389   0.0000   1.0000   1.0000
   0.250   0.0171   0.01606   0.00391   0.0018   1.0000   1.0000
   0.500   0.0341   0.01609   0.00397   0.0036   1.0000   1.0000
   0.750   0.0513   0.01613   0.00409   0.0054   1.0000   1.0000
   1.000   0.0684   0.01619   0.00423   0.0072   1.0000   1.0000
   1.250   0.0855   0.01627   0.00442   0.0090   1.0000   1.0000
   1.500   0.1029   0.01637   0.00465   0.0107   1.0000   1.0000
   1.750   0.1204   0.01649   0.00494   0.0124   1.0000   1.0000
   2.000   0.1382   0.01663   0.00535   0.0140   1.0000   1.0000
   2.250   0.1562   0.01679   0.00577   0.0155   1.0000   1.0000
   2.500   0.1745   0.01699   0.00625   0.0169   1.0000   1.0000
   2.750   0.1930   0.01721   0.00682   0.0183   1.0000   1.0000
   3.000   0.2117   0.01747   0.00757   0.0197   1.0000   1.0000
   3.250   0.3796   0.02318   0.01055  -0.0033   0.0564   1.0000
   3.500   0.4070   0.02490   0.01253  -0.0027   0.0447   1.0000
   3.750   0.4363   0.02685   0.01484  -0.0017   0.0406   1.0000
   4.000   0.4621   0.02910   0.01729  -0.0008   0.0368   1.0000
   4.250   0.4869   0.03146   0.02016   0.0005   0.0336   1.0000
   4.500   0.5102   0.03409   0.02331   0.0022   0.0325   1.0000
   4.750   0.5312   0.03698   0.02670   0.0040   0.0325   1.0000
   5.000   0.5499   0.04005   0.03027   0.0059   0.0329   1.0000
   5.250   0.5664   0.04331   0.03397   0.0079   0.0335   1.0000
   5.500   0.5811   0.04670   0.03782   0.0097   0.0340   1.0000
   5.750   0.5941   0.05020   0.04169   0.0115   0.0343   1.0000
   6.000   0.6056   0.05381   0.04563   0.0131   0.0344   1.0000
   6.250   0.6155   0.05754   0.04966   0.0145   0.0346   1.0000
   6.500   0.6239   0.06141   0.05376   0.0157   0.0349   1.0000
   6.750   0.6313   0.06558   0.05803   0.0167   0.0355   1.0000
   7.250   0.5725   0.06145   0.05497   0.0211   0.0427   1.0000
   7.500   0.5698   0.06590   0.05946   0.0217   0.0442   1.0000
   7.750   0.5599   0.07073   0.06441   0.0205   0.0524   1.0000
   8.000   0.5524   0.07504   0.06870   0.0206   0.0557   1.0000
   8.500   0.6484   0.09926   0.09261   0.0049   0.1085   1.0000
   8.750   0.6458   0.10321   0.09650   0.0026   0.1049   1.0000
   9.000   0.6533   0.10748   0.10077   0.0035   0.1011   1.0000
   9.250   0.6611   0.11279   0.10604   0.0045   0.0990   1.0000
   9.500   0.6443   0.11537   0.10848  -0.0024   0.0956   1.0000
   9.750   0.6434   0.11906   0.11212  -0.0045   0.0919   1.0000
  10.000   0.6474   0.12304   0.11608  -0.0051   0.0888   1.0000
  10.250   0.6656   0.12963   0.12271  -0.0013   0.0855   1.0000
  10.500   0.6580   0.13242   0.12541  -0.0056   0.0849   1.0000
  10.750   0.6504   0.13491   0.12781  -0.0098   0.0825   1.0000
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