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NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-209 (naca64209-il)
Reynolds number: 100,000
Max Cl/Cd: 45.86 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64209-il-100000.txt
Download as CSV file: xf-naca64209-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5412   0.10168   0.09669  -0.0127   1.0000   0.0989
  -9.250  -0.5507   0.09772   0.09283  -0.0172   1.0000   0.1034
  -9.000  -0.5737   0.09294   0.08817  -0.0254   1.0000   0.1046
  -8.750  -0.5429   0.08998   0.08516  -0.0183   1.0000   0.1129
  -8.500  -0.5582   0.08546   0.08074  -0.0239   1.0000   0.1171
  -8.250  -0.5851   0.08036   0.07567  -0.0317   1.0000   0.1182
  -8.000  -0.5598   0.07753   0.07293  -0.0262   1.0000   0.1271
  -7.750  -0.5817   0.07257   0.06788  -0.0335   1.0000   0.1317
  -7.500  -0.5676   0.06919   0.06458  -0.0312   1.0000   0.1417
  -7.250  -0.5687   0.06529   0.06066  -0.0325   1.0000   0.1523
  -7.000  -0.5667   0.06180   0.05715  -0.0330   1.0000   0.1659
  -6.500  -0.5547   0.05559   0.05087  -0.0322   1.0000   0.1978
  -6.250  -0.5518   0.05253   0.04774  -0.0318   1.0000   0.2205
  -5.500  -0.4892   0.03407   0.02610  -0.0339   1.0000   0.0774
  -5.250  -0.4709   0.02982   0.02175  -0.0329   1.0000   0.0737
  -5.000  -0.4507   0.02709   0.01863  -0.0314   1.0000   0.0718
  -4.750  -0.4300   0.02540   0.01650  -0.0298   1.0000   0.0755
  -4.500  -0.4090   0.02311   0.01393  -0.0284   1.0000   0.0793
  -4.250  -0.3884   0.02150   0.01227  -0.0271   1.0000   0.0852
  -4.000  -0.3680   0.02039   0.01102  -0.0259   1.0000   0.0938
  -3.750  -0.3479   0.01952   0.01011  -0.0248   1.0000   0.1010
  -3.500  -0.3271   0.01875   0.00926  -0.0236   1.0000   0.1030
  -3.250  -0.3068   0.01802   0.00852  -0.0224   1.0000   0.1034
  -3.000  -0.2867   0.01744   0.00794  -0.0212   1.0000   0.1042
  -2.750  -0.2664   0.01699   0.00746  -0.0202   1.0000   0.1051
  -2.500  -0.2459   0.01650   0.00695  -0.0195   1.0000   0.1076
  -2.250  -0.2249   0.01619   0.00661  -0.0189   1.0000   0.1116
  -2.000  -0.2038   0.01598   0.00634  -0.0183   1.0000   0.1183
  -1.750  -0.1824   0.01561   0.00612  -0.0179   1.0000   0.1407
  -1.500  -0.1677   0.01358   0.00647  -0.0162   1.0000   0.6624
  -1.250  -0.1403   0.01384   0.00704  -0.0151   0.9916   0.7794
  -1.000  -0.1098   0.01423   0.00749  -0.0147   0.9824   0.8444
  -0.750  -0.0815   0.01446   0.00773  -0.0141   0.9723   0.8883
  -0.500  -0.0454   0.01466   0.00790  -0.0152   0.9641   0.9326
  -0.250   0.0092   0.01485   0.00801  -0.0207   0.9580   0.9598
   0.000   0.0921   0.01503   0.00809  -0.0315   0.9573   1.0000
   0.250   0.1268   0.01514   0.00814  -0.0342   0.9465   1.0000
   0.500   0.1670   0.01529   0.00824  -0.0376   0.9376   1.0000
   0.750   0.2072   0.01543   0.00836  -0.0409   0.9289   1.0000
   1.000   0.2404   0.01560   0.00853  -0.0428   0.9187   1.0000
   1.250   0.2893   0.01569   0.00865  -0.0473   0.9128   1.0000
   1.500   0.3171   0.01590   0.00888  -0.0480   0.9016   1.0000
   1.750   0.3480   0.01612   0.00917  -0.0491   0.8916   1.0000
   2.000   0.3899   0.01619   0.00932  -0.0518   0.8844   1.0000
   2.250   0.4172   0.01640   0.00960  -0.0520   0.8725   1.0000
   2.500   0.4458   0.01660   0.00989  -0.0522   0.8611   1.0000
   2.750   0.4762   0.01675   0.01019  -0.0526   0.8503   1.0000
   3.000   0.5075   0.01670   0.01027  -0.0525   0.8373   1.0000
   3.250   0.5378   0.01565   0.00930  -0.0494   0.8084   1.0000
   3.500   0.5589   0.01430   0.00790  -0.0438   0.7631   1.0000
   3.750   0.5807   0.01374   0.00736  -0.0404   0.7256   1.0000
   4.000   0.6015   0.01343   0.00708  -0.0375   0.6787   1.0000
   4.250   0.6132   0.01337   0.00642  -0.0319   0.5018   1.0000
   4.500   0.6089   0.01720   0.00775  -0.0272   0.1249   1.0000
   4.750   0.6274   0.01865   0.00903  -0.0257   0.0986   1.0000
   5.000   0.6478   0.02001   0.01034  -0.0245   0.0856   1.0000
   5.250   0.6704   0.02180   0.01197  -0.0234   0.0790   1.0000
   5.500   0.6967   0.02321   0.01345  -0.0228   0.0724   1.0000
   5.750   0.7236   0.02564   0.01573  -0.0227   0.0669   1.0000
   6.000   0.7518   0.02757   0.01794  -0.0221   0.0655   1.0000
   6.250   0.7790   0.03000   0.02072  -0.0215   0.0651   1.0000
   6.500   0.8045   0.03284   0.02392  -0.0207   0.0653   1.0000
   6.750   0.8271   0.03539   0.02694  -0.0195   0.0639   1.0000
   7.000   0.8479   0.03881   0.03078  -0.0184   0.0648   1.0000
   7.250   0.8670   0.04336   0.03618  -0.0161   0.0750   1.0000
   8.500   0.8545   0.07666   0.07232  -0.0163   0.1720   1.0000
   8.750   0.8761   0.08086   0.07644  -0.0148   0.1615   1.0000
   9.000   0.8284   0.08542   0.08109  -0.0178   0.1594   1.0000
   9.250   0.7991   0.09205   0.08767  -0.0241   0.1551   1.0000
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