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NACA 0006 (naca0006-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0006 (naca0006-il)
Reynolds number: 50,000
Max Cl/Cd: 22.84 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0006-il-50000-n5.txt
Download as CSV file: xf-naca0006-il-50000-n5.csv

 
  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0006                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.7042   0.09180   0.08516   0.0035   1.0000   0.0398
  -8.500  -0.7055   0.08682   0.08020   0.0010   1.0000   0.0395
  -8.250  -0.7061   0.08170   0.07504  -0.0017   1.0000   0.0392
  -8.000  -0.7060   0.07655   0.06982  -0.0041   1.0000   0.0389
  -7.750  -0.7048   0.07139   0.06454  -0.0063   1.0000   0.0386
  -7.500  -0.7016   0.06624   0.05920  -0.0081   1.0000   0.0383
  -7.250  -0.6960   0.06114   0.05384  -0.0095   1.0000   0.0380
  -7.000  -0.6878   0.05610   0.04845  -0.0104   1.0000   0.0378
  -6.750  -0.6766   0.05127   0.04318  -0.0108   1.0000   0.0378
  -6.500  -0.6623   0.04669   0.03808  -0.0108   1.0000   0.0380
  -6.250  -0.6451   0.04252   0.03320  -0.0104   1.0000   0.0393
  -6.000  -0.6270   0.03891   0.02922  -0.0100   1.0000   0.0422
  -5.750  -0.6057   0.03598   0.02593  -0.0095   1.0000   0.0452
  -5.500  -0.5820   0.03284   0.02223  -0.0086   1.0000   0.0475
  -5.250  -0.5569   0.03021   0.01896  -0.0078   1.0000   0.0528
  -5.000  -0.5329   0.02801   0.01661  -0.0071   1.0000   0.0599
  -4.750  -0.5072   0.02591   0.01423  -0.0061   1.0000   0.0680
  -4.500  -0.4825   0.02429   0.01246  -0.0053   1.0000   0.0817
  -4.250  -0.4574   0.02271   0.01069  -0.0043   1.0000   0.0938
  -4.000  -0.4327   0.02137   0.00934  -0.0038   1.0000   0.1202
  -3.750  -0.4087   0.01978   0.00791  -0.0033   1.0000   0.1583
  -3.500  -0.3881   0.01792   0.00685  -0.0025   1.0000   0.2999
  -3.250  -0.3731   0.01634   0.00646   0.0003   1.0000   0.5394
  -3.000  -0.3543   0.01551   0.00658   0.0053   1.0000   0.7856
  -2.750  -0.2956   0.01553   0.00629   0.0021   1.0000   0.9329
  -2.500  -0.2247   0.01532   0.00551  -0.0062   1.0000   0.9906
  -2.250  -0.1933   0.01503   0.00489  -0.0078   1.0000   1.0000
  -2.000  -0.1723   0.01481   0.00445  -0.0071   1.0000   1.0000
  -1.750  -0.1511   0.01464   0.00409  -0.0063   1.0000   1.0000
  -1.500  -0.1297   0.01450   0.00379  -0.0055   1.0000   1.0000
  -1.250  -0.1081   0.01439   0.00352  -0.0047   1.0000   1.0000
  -1.000  -0.0866   0.01431   0.00332  -0.0038   1.0000   1.0000
  -0.750  -0.0650   0.01424   0.00318  -0.0029   1.0000   1.0000
  -0.500  -0.0434   0.01420   0.00307  -0.0019   1.0000   1.0000
  -0.250  -0.0217   0.01417   0.00300  -0.0010   1.0000   1.0000
   0.000   0.0000   0.01416   0.00298   0.0000   1.0000   1.0000
   0.250   0.0217   0.01417   0.00300   0.0010   1.0000   1.0000
   0.500   0.0434   0.01420   0.00307   0.0019   1.0000   1.0000
   0.750   0.0650   0.01424   0.00317   0.0028   1.0000   1.0000
   1.000   0.0866   0.01430   0.00332   0.0038   1.0000   1.0000
   1.250   0.1082   0.01439   0.00352   0.0047   1.0000   1.0000
   1.500   0.1297   0.01450   0.00379   0.0055   1.0000   1.0000
   1.750   0.1512   0.01464   0.00409   0.0063   1.0000   1.0000
   2.000   0.1724   0.01481   0.00445   0.0071   1.0000   1.0000
   2.250   0.1934   0.01503   0.00488   0.0077   1.0000   1.0000
   2.500   0.2247   0.01532   0.00551   0.0062   0.9907   1.0000
   2.750   0.2956   0.01553   0.00629  -0.0021   0.9330   1.0000
   3.000   0.3543   0.01551   0.00658  -0.0053   0.7856   1.0000
   3.250   0.3731   0.01634   0.00646  -0.0003   0.5397   1.0000
   3.500   0.3881   0.01792   0.00685   0.0025   0.3002   1.0000
   3.750   0.4087   0.01978   0.00791   0.0033   0.1583   1.0000
   4.000   0.4327   0.02137   0.00934   0.0038   0.1202   1.0000
   4.250   0.4574   0.02271   0.01069   0.0043   0.0938   1.0000
   4.500   0.4825   0.02429   0.01246   0.0053   0.0817   1.0000
   4.750   0.5072   0.02591   0.01423   0.0061   0.0680   1.0000
   5.000   0.5329   0.02801   0.01662   0.0071   0.0599   1.0000
   5.250   0.5570   0.03022   0.01896   0.0077   0.0528   1.0000
   5.500   0.5821   0.03284   0.02224   0.0086   0.0475   1.0000
   5.750   0.6058   0.03598   0.02593   0.0095   0.0452   1.0000
   6.000   0.6270   0.03891   0.02922   0.0100   0.0421   1.0000
   6.250   0.6451   0.04252   0.03321   0.0104   0.0393   1.0000
   6.500   0.6624   0.04670   0.03809   0.0108   0.0380   1.0000
   6.750   0.6767   0.05128   0.04319   0.0108   0.0378   1.0000
   7.000   0.6880   0.05611   0.04846   0.0103   0.0378   1.0000
   7.250   0.6962   0.06115   0.05385   0.0094   0.0380   1.0000
   7.500   0.7018   0.06626   0.05922   0.0081   0.0383   1.0000
   7.750   0.7050   0.07141   0.06456   0.0063   0.0386   1.0000
   8.000   0.7063   0.07658   0.06985   0.0041   0.0389   1.0000
   8.250   0.7064   0.08173   0.07507   0.0016   0.0392   1.0000
   8.500   0.7059   0.08685   0.08023  -0.0010   0.0395   1.0000
   8.750   0.7046   0.09184   0.08520  -0.0036   0.0398   1.0000
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