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NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A410 (naca64a410-il)
Reynolds number: 100,000
Max Cl/Cd: 55.55 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a410-il-100000-n5.txt
Download as CSV file: xf-naca64a410-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A410                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4247   0.09447   0.08944  -0.0412   1.0000   0.0338
  -8.750  -0.4492   0.08219   0.07735  -0.0491   1.0000   0.0275
  -8.500  -0.4594   0.07920   0.07444  -0.0485   1.0000   0.0272
  -8.250  -0.4737   0.07611   0.07144  -0.0483   1.0000   0.0270
  -8.000  -0.4864   0.07274   0.06810  -0.0483   1.0000   0.0268
  -7.750  -0.4982   0.06935   0.06470  -0.0479   1.0000   0.0267
  -7.500  -0.5082   0.06570   0.06100  -0.0475   1.0000   0.0266
  -7.250  -0.5153   0.06176   0.05695  -0.0472   1.0000   0.0266
  -7.000  -0.5036   0.05547   0.05028  -0.0516   0.9958   0.0271
  -6.750  -0.4824   0.04952   0.04377  -0.0561   0.9901   0.0276
  -6.500  -0.4583   0.04439   0.03815  -0.0595   0.9857   0.0276
  -6.250  -0.4347   0.04001   0.03324  -0.0616   0.9803   0.0276
  -6.000  -0.4064   0.03586   0.02851  -0.0639   0.9764   0.0279
  -5.750  -0.3807   0.03258   0.02489  -0.0653   0.9717   0.0289
  -5.500  -0.3510   0.03084   0.02297  -0.0670   0.9674   0.0314
  -5.250  -0.3172   0.02856   0.02019  -0.0688   0.9644   0.0334
  -5.000  -0.2887   0.02652   0.01771  -0.0692   0.9593   0.0344
  -4.750  -0.2564   0.02480   0.01560  -0.0701   0.9552   0.0357
  -4.500  -0.2219   0.02333   0.01387  -0.0716   0.9522   0.0388
  -4.250  -0.1909   0.02204   0.01252  -0.0726   0.9481   0.0417
  -4.000  -0.1617   0.02100   0.01139  -0.0730   0.9428   0.0442
  -3.750  -0.1281   0.02008   0.01035  -0.0743   0.9390   0.0475
  -3.500  -0.0928   0.01911   0.00936  -0.0762   0.9362   0.0546
  -2.750  -0.0003   0.01722   0.00760  -0.0787   0.9209   0.1312
  -2.500   0.0231   0.01573   0.00727  -0.0791   0.9139   0.3792
  -2.250   0.0512   0.01518   0.00735  -0.0789   0.9093   0.5831
  -2.000   0.0763   0.01508   0.00741  -0.0779   0.9030   0.6648
  -1.750   0.1016   0.01501   0.00743  -0.0768   0.8967   0.7240
  -1.500   0.1311   0.01488   0.00731  -0.0765   0.8927   0.7682
  -1.250   0.1537   0.01482   0.00723  -0.0752   0.8843   0.7951
  -1.000   0.1842   0.01469   0.00705  -0.0754   0.8796   0.8168
  -0.750   0.2095   0.01461   0.00698  -0.0746   0.8723   0.8396
  -0.500   0.2395   0.01448   0.00685  -0.0747   0.8667   0.8658
  -0.250   0.2740   0.01437   0.00673  -0.0758   0.8619   0.8956
   0.000   0.3120   0.01430   0.00666  -0.0779   0.8545   0.9400
   0.250   0.3560   0.01412   0.00642  -0.0812   0.8493   1.0000
   0.500   0.3805   0.01417   0.00639  -0.0807   0.8387   1.0000
   0.750   0.4084   0.01412   0.00628  -0.0808   0.8292   1.0000
   1.000   0.4381   0.01402   0.00613  -0.0810   0.8202   1.0000
   1.250   0.4634   0.01404   0.00611  -0.0805   0.8087   1.0000
   1.500   0.4903   0.01405   0.00610  -0.0802   0.7987   1.0000
   1.750   0.5197   0.01402   0.00606  -0.0804   0.7915   1.0000
   2.000   0.5453   0.01414   0.00621  -0.0801   0.7818   1.0000
   2.250   0.5735   0.01417   0.00625  -0.0801   0.7736   1.0000
   2.500   0.6013   0.01419   0.00629  -0.0799   0.7640   1.0000
   2.750   0.6278   0.01427   0.00644  -0.0796   0.7533   1.0000
   3.000   0.6556   0.01433   0.00655  -0.0795   0.7440   1.0000
   3.250   0.6836   0.01438   0.00666  -0.0793   0.7343   1.0000
   3.500   0.7098   0.01449   0.00684  -0.0789   0.7220   1.0000
   3.750   0.7367   0.01449   0.00691  -0.0783   0.7053   1.0000
   4.000   0.7610   0.01451   0.00693  -0.0772   0.6790   1.0000
   4.250   0.7851   0.01453   0.00691  -0.0758   0.6460   1.0000
   4.500   0.8074   0.01465   0.00696  -0.0743   0.6038   1.0000
   4.750   0.8288   0.01492   0.00712  -0.0727   0.5511   1.0000
   5.000   0.8489   0.01535   0.00735  -0.0710   0.4861   1.0000
   5.250   0.8596   0.01649   0.00774  -0.0679   0.3451   1.0000
   5.500   0.8660   0.01833   0.00869  -0.0649   0.2017   1.0000
   5.750   0.8775   0.01988   0.00969  -0.0628   0.1272   1.0000
   6.000   0.8945   0.02092   0.01066  -0.0612   0.0862   1.0000
   6.250   0.9106   0.02202   0.01148  -0.0596   0.0590   1.0000
   6.500   0.9250   0.02328   0.01269  -0.0576   0.0510   1.0000
   6.750   0.9410   0.02435   0.01390  -0.0558   0.0449   1.0000
   7.000   0.9531   0.02581   0.01539  -0.0537   0.0406   1.0000
   7.250   0.9689   0.02703   0.01672  -0.0519   0.0384   1.0000
   7.500   0.9859   0.02830   0.01816  -0.0503   0.0364   1.0000
   7.750   1.0044   0.02972   0.01967  -0.0490   0.0347   1.0000
   8.000   1.0246   0.03124   0.02128  -0.0480   0.0330   1.0000
   8.250   1.0449   0.03289   0.02296  -0.0472   0.0310   1.0000
   8.500   1.0678   0.03505   0.02521  -0.0468   0.0291   1.0000
   8.750   1.0907   0.03693   0.02740  -0.0461   0.0282   1.0000
   9.000   1.1123   0.03917   0.02995  -0.0452   0.0274   1.0000
   9.250   1.1310   0.04167   0.03280  -0.0441   0.0267   1.0000
   9.500   1.1459   0.04440   0.03592  -0.0425   0.0262   1.0000
   9.750   1.1563   0.04728   0.03919  -0.0405   0.0257   1.0000
  10.000   1.1626   0.04999   0.04226  -0.0382   0.0250   1.0000
  10.250   1.1663   0.05247   0.04501  -0.0359   0.0241   1.0000
  10.500   1.1681   0.05472   0.04746  -0.0335   0.0232   1.0000
  10.750   1.1654   0.05723   0.05018  -0.0308   0.0227   1.0000
  11.000   1.1586   0.06018   0.05341  -0.0280   0.0224   1.0000
  11.250   1.1479   0.06347   0.05697  -0.0254   0.0222   1.0000
  11.500   1.1343   0.06705   0.06081  -0.0233   0.0222   1.0000
  11.750   1.1182   0.07099   0.06500  -0.0217   0.0221   1.0000
  12.000   1.0996   0.07540   0.06966  -0.0209   0.0221   1.0000
  12.250   1.0786   0.08044   0.07496  -0.0212   0.0222   1.0000
  12.500   1.0544   0.08644   0.08120  -0.0227   0.0224   1.0000
  12.750   1.0269   0.09381   0.08877  -0.0259   0.0226   1.0000
  13.000   0.9836   0.10599   0.10122  -0.0337   0.0233   1.0000
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