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NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-206 (naca64206-il)
Reynolds number: 500,000
Max Cl/Cd: 72.2 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64206-il-500000.txt
Download as CSV file: xf-naca64206-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-206                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5356   0.08769   0.08545  -0.0105   1.0000   0.0096
  -8.000  -0.5345   0.08367   0.08146  -0.0130   1.0000   0.0096
  -7.750  -0.5362   0.07932   0.07715  -0.0163   1.0000   0.0096
  -7.500  -0.5319   0.07422   0.07203  -0.0222   1.0000   0.0096
  -7.250  -0.5255   0.06939   0.06715  -0.0259   1.0000   0.0096
  -7.000  -0.5178   0.06451   0.06220  -0.0290   1.0000   0.0096
  -6.750  -0.5179   0.05664   0.05421  -0.0326   1.0000   0.0099
  -6.500  -0.5132   0.05043   0.04785  -0.0348   1.0000   0.0103
  -6.250  -0.5022   0.04669   0.04400  -0.0358   1.0000   0.0109
  -6.000  -0.4871   0.04342   0.04056  -0.0365   1.0000   0.0115
  -5.750  -0.4703   0.04053   0.03754  -0.0368   1.0000   0.0130
  -5.500  -0.4508   0.03718   0.03398  -0.0369   1.0000   0.0147
  -5.250  -0.4199   0.03738   0.03394  -0.0354   1.0000   0.0179
  -5.000  -0.4002   0.03448   0.03077  -0.0349   1.0000   0.0180
  -4.750  -0.3805   0.03146   0.02748  -0.0343   1.0000   0.0181
  -4.500  -0.3658   0.02401   0.01953  -0.0344   1.0000   0.0197
  -4.250  -0.3451   0.02180   0.01717  -0.0338   1.0000   0.0208
  -4.000  -0.3234   0.01996   0.01515  -0.0330   1.0000   0.0220
  -3.750  -0.3006   0.01795   0.01287  -0.0319   1.0000   0.0225
  -3.500  -0.2742   0.01445   0.00890  -0.0300   1.0000   0.0149
  -3.250  -0.2505   0.01279   0.00698  -0.0288   1.0000   0.0156
  -3.000  -0.2157   0.01251   0.00660  -0.0302   0.9977   0.0179
  -2.750  -0.1820   0.01041   0.00437  -0.0315   0.9954   0.0196
  -2.500  -0.1467   0.00931   0.00320  -0.0333   0.9924   0.0224
  -2.250  -0.1108   0.00877   0.00261  -0.0351   0.9883   0.0266
  -2.000  -0.0737   0.00832   0.00206  -0.0372   0.9846   0.0324
  -1.750  -0.0383   0.00647   0.00145  -0.0400   0.9821   0.3975
  -1.250   0.0260   0.00522   0.00146  -0.0422   0.9713   0.7717
  -1.000   0.0559   0.00504   0.00150  -0.0422   0.9642   0.8409
  -0.750   0.0839   0.00494   0.00150  -0.0418   0.9560   0.8855
  -0.500   0.1090   0.00488   0.00147  -0.0407   0.9449   0.9143
  -0.250   0.1344   0.00482   0.00142  -0.0398   0.9334   0.9330
   0.000   0.1605   0.00477   0.00135  -0.0391   0.9218   0.9515
   0.250   0.1911   0.00473   0.00129  -0.0395   0.9108   0.9694
   0.500   0.2276   0.00470   0.00125  -0.0413   0.9002   0.9855
   0.750   0.2603   0.00471   0.00122  -0.0424   0.8871   1.0000
   1.000   0.2859   0.00476   0.00123  -0.0420   0.8697   1.0000
   1.250   0.3111   0.00483   0.00122  -0.0413   0.8465   1.0000
   1.500   0.3355   0.00493   0.00119  -0.0403   0.8085   1.0000
   1.750   0.3596   0.00511   0.00120  -0.0392   0.7550   1.0000
   2.000   0.3846   0.00534   0.00124  -0.0385   0.7004   1.0000
   2.250   0.4094   0.00567   0.00131  -0.0378   0.6288   1.0000
   2.500   0.4321   0.00635   0.00145  -0.0370   0.4890   1.0000
   2.750   0.4477   0.00887   0.00214  -0.0361   0.0545   1.0000
   3.000   0.4739   0.00950   0.00273  -0.0358   0.0295   1.0000
   3.250   0.5002   0.01012   0.00343  -0.0355   0.0236   1.0000
   3.500   0.5235   0.01153   0.00498  -0.0346   0.0210   1.0000
   3.750   0.5502   0.01198   0.00548  -0.0344   0.0197   1.0000
   4.000   0.5760   0.01276   0.00634  -0.0340   0.0181   1.0000
   4.250   0.6015   0.01390   0.00755  -0.0334   0.0163   1.0000
   4.500   0.6272   0.01563   0.00943  -0.0326   0.0157   1.0000
   4.750   0.6535   0.01776   0.01177  -0.0318   0.0156   1.0000
   5.000   0.6786   0.01850   0.01261  -0.0317   0.0131   1.0000
   5.250   0.7019   0.02203   0.01649  -0.0308   0.0123   1.0000
   5.500   0.7094   0.01514   0.01073  -0.0265   0.0156   1.0000
   5.750   0.7294   0.01835   0.01429  -0.0255   0.0149   1.0000
   6.000   0.7476   0.02156   0.01778  -0.0247   0.0141   1.0000
   6.250   0.7642   0.02501   0.02145  -0.0241   0.0134   1.0000
   6.500   0.7782   0.02894   0.02560  -0.0236   0.0129   1.0000
   6.750   0.7870   0.03425   0.03116  -0.0230   0.0124   1.0000
   7.000   0.7769   0.04460   0.04188  -0.0225   0.0118   1.0000
   7.250   0.7740   0.05162   0.04911  -0.0220   0.0117   1.0000
   7.500   0.7735   0.05687   0.05453  -0.0218   0.0117   1.0000
   7.750   0.7684   0.06203   0.05984  -0.0217   0.0117   1.0000
   8.000   0.7578   0.06677   0.06469  -0.0215   0.0116   1.0000
   8.250   0.7399   0.07091   0.06890  -0.0216   0.0116   1.0000
   8.500   0.7228   0.07611   0.07417  -0.0243   0.0117   1.0000
   8.750   0.7091   0.08291   0.08103  -0.0293   0.0117   1.0000
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