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NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A-010 10.0% (naca64a010-il)
Reynolds number: 100,000
Max Cl/Cd: 34.52 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a010-il-100000-n5.txt
Download as CSV file: xf-naca64a010-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A-010 10.0%                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6744   0.08761   0.08238  -0.0232   1.0000   0.0259
 -10.750  -0.6865   0.08151   0.07625  -0.0269   1.0000   0.0256
 -10.500  -0.7020   0.07584   0.07053  -0.0302   1.0000   0.0255
 -10.250  -0.7187   0.07096   0.06556  -0.0323   1.0000   0.0253
 -10.000  -0.7359   0.06681   0.06130  -0.0329   1.0000   0.0252
  -9.750  -0.7530   0.06319   0.05755  -0.0318   1.0000   0.0251
  -9.500  -0.7674   0.05989   0.05409  -0.0296   1.0000   0.0250
  -9.250  -0.7769   0.05632   0.05029  -0.0277   1.0000   0.0249
  -9.000  -0.7831   0.05267   0.04636  -0.0255   1.0000   0.0250
  -8.750  -0.7849   0.04917   0.04253  -0.0233   1.0000   0.0250
  -8.500  -0.7835   0.04576   0.03873  -0.0210   1.0000   0.0251
  -8.250  -0.7786   0.04252   0.03504  -0.0186   1.0000   0.0252
  -8.000  -0.7703   0.03952   0.03159  -0.0164   1.0000   0.0255
  -7.750  -0.7599   0.03664   0.02834  -0.0144   1.0000   0.0264
  -7.500  -0.7458   0.03468   0.02626  -0.0131   1.0000   0.0279
  -7.250  -0.7294   0.03291   0.02428  -0.0116   1.0000   0.0293
  -7.000  -0.7116   0.03084   0.02192  -0.0101   1.0000   0.0302
  -6.750  -0.6920   0.02883   0.01961  -0.0086   1.0000   0.0311
  -6.500  -0.6711   0.02704   0.01758  -0.0073   1.0000   0.0322
  -6.250  -0.6497   0.02547   0.01578  -0.0061   1.0000   0.0337
  -6.000  -0.6293   0.02412   0.01429  -0.0048   1.0000   0.0361
  -5.750  -0.6107   0.02290   0.01311  -0.0034   1.0000   0.0390
  -5.500  -0.5920   0.02180   0.01197  -0.0018   1.0000   0.0412
  -5.250  -0.5744   0.02080   0.01090   0.0001   1.0000   0.0439
  -5.000  -0.5581   0.01988   0.00989   0.0021   1.0000   0.0475
  -4.750  -0.5423   0.01909   0.00912   0.0040   1.0000   0.0535
  -4.500  -0.5262   0.01838   0.00832   0.0061   1.0000   0.0597
  -4.250  -0.5108   0.01764   0.00758   0.0082   1.0000   0.0700
  -4.000  -0.4960   0.01686   0.00693   0.0103   1.0000   0.0906
  -3.750  -0.4833   0.01586   0.00628   0.0126   1.0000   0.1515
  -3.500  -0.4783   0.01412   0.00573   0.0158   1.0000   0.3673
  -3.250  -0.4599   0.01332   0.00581   0.0174   0.9952   0.5670
  -3.000  -0.4281   0.01319   0.00592   0.0170   0.9868   0.6534
  -2.750  -0.3985   0.01326   0.00618   0.0175   0.9780   0.7256
  -2.500  -0.3689   0.01342   0.00638   0.0181   0.9693   0.7756
  -2.250  -0.3331   0.01346   0.00635   0.0168   0.9621   0.7954
  -2.000  -0.2971   0.01342   0.00620   0.0151   0.9541   0.8085
  -1.750  -0.2610   0.01337   0.00602   0.0134   0.9462   0.8202
  -1.500  -0.2218   0.01335   0.00591   0.0111   0.9392   0.8297
  -1.250  -0.1859   0.01331   0.00581   0.0094   0.9308   0.8399
  -1.000  -0.1480   0.01326   0.00569   0.0073   0.9234   0.8507
  -0.750  -0.1121   0.01325   0.00564   0.0057   0.9142   0.8601
  -0.500  -0.0733   0.01323   0.00559   0.0035   0.9067   0.8693
  -0.250  -0.0385   0.01321   0.00555   0.0021   0.8970   0.8798
   0.000   0.0000   0.01322   0.00556   0.0000   0.8882   0.8882
   0.250   0.0385   0.01321   0.00555  -0.0021   0.8798   0.8969
   0.500   0.0733   0.01323   0.00559  -0.0035   0.8693   0.9067
   0.750   0.1121   0.01325   0.00564  -0.0057   0.8600   0.9142
   1.000   0.1480   0.01326   0.00569  -0.0073   0.8507   0.9234
   1.250   0.1859   0.01331   0.00581  -0.0094   0.8399   0.9308
   1.500   0.2219   0.01335   0.00592  -0.0111   0.8297   0.9393
   1.750   0.2610   0.01337   0.00602  -0.0134   0.8201   0.9461
   2.000   0.2971   0.01342   0.00620  -0.0151   0.8085   0.9541
   2.250   0.3332   0.01346   0.00634  -0.0168   0.7954   0.9620
   2.500   0.3688   0.01342   0.00638  -0.0181   0.7755   0.9693
   2.750   0.3985   0.01326   0.00618  -0.0175   0.7254   0.9780
   3.000   0.4282   0.01319   0.00592  -0.0170   0.6539   0.9868
   3.250   0.4598   0.01332   0.00581  -0.0174   0.5664   0.9952
   3.500   0.4784   0.01412   0.00573  -0.0158   0.3680   1.0000
   3.750   0.4834   0.01586   0.00628  -0.0126   0.1514   1.0000
   4.000   0.4961   0.01685   0.00693  -0.0104   0.0908   1.0000
   4.250   0.5109   0.01764   0.00759  -0.0082   0.0697   1.0000
   4.500   0.5263   0.01838   0.00832  -0.0061   0.0597   1.0000
   4.750   0.5424   0.01909   0.00912  -0.0041   0.0533   1.0000
   5.000   0.5581   0.01989   0.00990  -0.0021   0.0474   1.0000
   5.250   0.5745   0.02081   0.01090  -0.0001   0.0438   1.0000
   5.500   0.5920   0.02180   0.01197   0.0018   0.0412   1.0000
   5.750   0.6107   0.02290   0.01311   0.0034   0.0388   1.0000
   6.000   0.6293   0.02413   0.01430   0.0047   0.0361   1.0000
   6.250   0.6497   0.02548   0.01578   0.0061   0.0336   1.0000
   6.500   0.6711   0.02704   0.01758   0.0073   0.0322   1.0000
   6.750   0.6920   0.02884   0.01962   0.0086   0.0311   1.0000
   7.000   0.7116   0.03085   0.02193   0.0101   0.0301   1.0000
   7.250   0.7294   0.03288   0.02425   0.0116   0.0292   1.0000
   7.500   0.7457   0.03460   0.02615   0.0130   0.0277   1.0000
   7.750   0.7602   0.03662   0.02834   0.0144   0.0265   1.0000
   8.000   0.7703   0.03955   0.03161   0.0163   0.0256   1.0000
   8.250   0.7786   0.04250   0.03502   0.0186   0.0252   1.0000
   8.500   0.7835   0.04575   0.03873   0.0210   0.0251   1.0000
   8.750   0.7850   0.04917   0.04252   0.0233   0.0250   1.0000
   9.000   0.7830   0.05271   0.04640   0.0255   0.0249   1.0000
   9.250   0.7774   0.05628   0.05025   0.0276   0.0250   1.0000
   9.500   0.7671   0.05994   0.05414   0.0296   0.0250   1.0000
   9.750   0.7539   0.06315   0.05750   0.0317   0.0251   1.0000
  10.000   0.7363   0.06680   0.06128   0.0328   0.0252   1.0000
  10.250   0.7197   0.07092   0.06551   0.0323   0.0253   1.0000
  10.500   0.7026   0.07583   0.07052   0.0301   0.0255   1.0000
  10.750   0.6868   0.08157   0.07631   0.0268   0.0257   1.0000
  11.000   0.6753   0.08757   0.08233   0.0232   0.0259   1.0000
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