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NACA 1408 (naca1408-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 1408 (naca1408-il)
Reynolds number: 50,000
Max Cl/Cd: 31.5 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca1408-il-50000-n5.txt
Download as CSV file: xf-naca1408-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1408                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6252   0.10687   0.09980  -0.0050   1.0000   0.0513
  -9.750  -0.6249   0.10194   0.09491  -0.0071   1.0000   0.0511
  -9.500  -0.6252   0.09694   0.08995  -0.0094   1.0000   0.0509
  -9.250  -0.6266   0.09169   0.08470  -0.0123   1.0000   0.0506
  -9.000  -0.6298   0.08595   0.07900  -0.0162   1.0000   0.0502
  -8.750  -0.6359   0.08001   0.07315  -0.0205   1.0000   0.0498
  -8.500  -0.6417   0.07420   0.06729  -0.0240   1.0000   0.0495
  -8.250  -0.6469   0.06849   0.06145  -0.0269   1.0000   0.0493
  -8.000  -0.6498   0.06289   0.05564  -0.0290   1.0000   0.0493
  -7.750  -0.6501   0.05740   0.04978  -0.0304   1.0000   0.0499
  -7.500  -0.6472   0.05208   0.04389  -0.0312   1.0000   0.0510
  -7.250  -0.6366   0.04844   0.04002  -0.0310   1.0000   0.0533
  -7.000  -0.6222   0.04537   0.03670  -0.0306   1.0000   0.0556
  -6.750  -0.6075   0.04164   0.03250  -0.0301   1.0000   0.0574
  -6.500  -0.5905   0.03837   0.02866  -0.0294   1.0000   0.0614
  -6.250  -0.5715   0.03532   0.02500  -0.0286   1.0000   0.0657
  -6.000  -0.5505   0.03302   0.02250  -0.0279   1.0000   0.0693
  -5.750  -0.5282   0.03104   0.02010  -0.0270   1.0000   0.0758
  -5.500  -0.5056   0.02918   0.01803  -0.0263   1.0000   0.0820
  -5.250  -0.4817   0.02746   0.01603  -0.0253   1.0000   0.0871
  -5.000  -0.4574   0.02591   0.01423  -0.0243   1.0000   0.0933
  -4.750  -0.4342   0.02480   0.01302  -0.0235   1.0000   0.1046
  -4.500  -0.4108   0.02358   0.01179  -0.0226   1.0000   0.1142
  -4.250  -0.3870   0.02243   0.01054  -0.0217   1.0000   0.1264
  -4.000  -0.3628   0.02133   0.00942  -0.0210   1.0000   0.1476
  -3.750  -0.3403   0.02024   0.00856  -0.0204   1.0000   0.1898
  -3.500  -0.3189   0.01912   0.00788  -0.0196   1.0000   0.2680
  -3.000  -0.2822   0.01702   0.00714  -0.0160   1.0000   0.5337
  -2.750  -0.2650   0.01635   0.00702  -0.0127   1.0000   0.6734
  -2.500  -0.2388   0.01599   0.00697  -0.0102   1.0000   0.8165
  -2.250  -0.1788   0.01591   0.00667  -0.0150   1.0000   0.9424
  -2.000  -0.1158   0.01576   0.00613  -0.0223   1.0000   1.0000
  -1.750  -0.1017   0.01564   0.00581  -0.0204   1.0000   1.0000
  -1.500  -0.0865   0.01557   0.00557  -0.0186   1.0000   1.0000
  -1.250  -0.0702   0.01555   0.00538  -0.0169   1.0000   1.0000
  -1.000  -0.0528   0.01556   0.00526  -0.0154   1.0000   1.0000
  -0.750  -0.0347   0.01561   0.00517  -0.0141   1.0000   1.0000
  -0.500  -0.0160   0.01568   0.00514  -0.0128   1.0000   1.0000
  -0.250   0.0032   0.01580   0.00517  -0.0117   1.0000   1.0000
   0.000   0.0227   0.01595   0.00525  -0.0108   1.0000   1.0000
   0.250   0.0424   0.01613   0.00537  -0.0099   1.0000   1.0000
   0.500   0.0622   0.01636   0.00556  -0.0091   1.0000   1.0000
   0.750   0.0864   0.01664   0.00583  -0.0093   0.9975   1.0000
   1.000   0.1335   0.01696   0.00617  -0.0139   0.9820   1.0000
   1.250   0.1802   0.01723   0.00649  -0.0182   0.9656   1.0000
   1.500   0.2260   0.01745   0.00681  -0.0221   0.9482   1.0000
   1.750   0.2704   0.01762   0.00709  -0.0256   0.9291   1.0000
   2.000   0.3146   0.01772   0.00736  -0.0287   0.9095   1.0000
   2.250   0.3534   0.01779   0.00757  -0.0306   0.8863   1.0000
   2.500   0.3913   0.01781   0.00775  -0.0320   0.8619   1.0000
   2.750   0.4257   0.01782   0.00794  -0.0325   0.8348   1.0000
   3.000   0.4567   0.01785   0.00810  -0.0322   0.8043   1.0000
   3.250   0.4855   0.01790   0.00826  -0.0313   0.7703   1.0000
   3.500   0.5129   0.01795   0.00841  -0.0300   0.7332   1.0000
   3.750   0.5377   0.01807   0.00856  -0.0282   0.6903   1.0000
   4.000   0.5603   0.01827   0.00873  -0.0260   0.6383   1.0000
   4.250   0.5813   0.01857   0.00891  -0.0235   0.5765   1.0000
   4.500   0.5997   0.01904   0.00910  -0.0208   0.4947   1.0000
   4.750   0.6164   0.01981   0.00940  -0.0183   0.3895   1.0000
   5.000   0.6339   0.02098   0.01000  -0.0167   0.2753   1.0000
   5.250   0.6518   0.02263   0.01106  -0.0156   0.1794   1.0000
   5.500   0.6718   0.02424   0.01236  -0.0147   0.1344   1.0000
   5.750   0.6929   0.02570   0.01377  -0.0138   0.1151   1.0000
   6.000   0.7148   0.02712   0.01528  -0.0127   0.1037   1.0000
   6.250   0.7375   0.02865   0.01688  -0.0116   0.0958   1.0000
   6.500   0.7598   0.03011   0.01843  -0.0108   0.0861   1.0000
   6.750   0.7840   0.03180   0.02040  -0.0099   0.0789   1.0000
   7.000   0.8077   0.03374   0.02245  -0.0091   0.0736   1.0000
   7.250   0.8300   0.03587   0.02490  -0.0083   0.0670   1.0000
   7.500   0.8514   0.03817   0.02751  -0.0074   0.0620   1.0000
   7.750   0.8709   0.04095   0.03033  -0.0067   0.0583   1.0000
   8.000   0.8865   0.04394   0.03410  -0.0052   0.0542   1.0000
   8.250   0.8998   0.04729   0.03795  -0.0040   0.0514   1.0000
   8.500   0.9104   0.05090   0.04205  -0.0028   0.0497   1.0000
   8.750   0.9199   0.05410   0.04551  -0.0018   0.0476   1.0000
   9.000   0.9259   0.05788   0.04940  -0.0009   0.0457   1.0000
   9.250   0.9206   0.06231   0.05440   0.0003   0.0448   1.0000
   9.500   0.9110   0.06696   0.05946   0.0010   0.0443   1.0000
   9.750   0.8974   0.07168   0.06447   0.0012   0.0441   1.0000
  10.000   0.8796   0.07631   0.06927   0.0011   0.0442   1.0000
  10.250   0.8614   0.08164   0.07471  -0.0010   0.0445   1.0000
  10.500   0.8442   0.08790   0.08104  -0.0049   0.0448   1.0000
  10.750   0.8295   0.09495   0.08812  -0.0098   0.0451   1.0000
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