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NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-206 (naca65206-il)
Reynolds number: 100,000
Max Cl/Cd: 40.22 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65206-il-100000.txt
Download as CSV file: xf-naca65206-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-206                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5478   0.08948   0.08466  -0.0128   1.0000   0.0662
  -7.750  -0.5505   0.08587   0.08113  -0.0159   1.0000   0.0682
  -7.500  -0.5514   0.08161   0.07687  -0.0230   1.0000   0.0701
  -7.250  -0.5523   0.07840   0.07345  -0.0307   1.0000   0.0713
  -7.000  -0.5433   0.07248   0.06771  -0.0283   1.0000   0.0740
  -6.750  -0.5341   0.06894   0.06417  -0.0281   1.0000   0.0788
  -6.250  -0.5167   0.06061   0.05565  -0.0327   1.0000   0.0892
  -6.000  -0.5050   0.05724   0.05189  -0.0359   1.0000   0.0992
  -5.750  -0.4919   0.05342   0.04823  -0.0346   1.0000   0.1072
  -5.500  -0.4771   0.05073   0.04518  -0.0361   1.0000   0.1240
  -5.250  -0.4642   0.04688   0.04125  -0.0362   1.0000   0.1397
  -5.000  -0.4503   0.04354   0.03801  -0.0351   1.0000   0.1570
  -4.750  -0.4364   0.04091   0.03535  -0.0343   1.0000   0.1876
  -3.750  -0.3192   0.02742   0.01925  -0.0338   1.0000   0.0970
  -3.500  -0.2891   0.02490   0.01600  -0.0319   1.0000   0.0712
  -3.250  -0.2646   0.02183   0.01278  -0.0309   1.0000   0.0659
  -3.000  -0.2391   0.01993   0.01054  -0.0296   1.0000   0.0625
  -2.750  -0.2148   0.01840   0.00887  -0.0283   1.0000   0.0637
  -2.500  -0.1912   0.01746   0.00778  -0.0272   1.0000   0.0721
  -2.250  -0.1689   0.01590   0.00636  -0.0260   1.0000   0.0760
  -2.000  -0.1464   0.01497   0.00540  -0.0249   1.0000   0.0834
  -1.750  -0.1230   0.01403   0.00441  -0.0241   1.0000   0.1025
  -1.500  -0.1001   0.01066   0.00423  -0.0193   1.0000   1.0000
  -1.250  -0.0823   0.01066   0.00390  -0.0180   1.0000   1.0000
  -1.000  -0.0621   0.01069   0.00369  -0.0173   1.0000   1.0000
  -0.750  -0.0409   0.01077   0.00357  -0.0167   1.0000   1.0000
  -0.500  -0.0192   0.01088   0.00352  -0.0162   1.0000   1.0000
  -0.250   0.0027   0.01101   0.00349  -0.0158   1.0000   1.0000
   0.000   0.0245   0.01118   0.00355  -0.0154   1.0000   1.0000
   0.250   0.0463   0.01137   0.00366  -0.0150   1.0000   1.0000
   0.500   0.0680   0.01160   0.00382  -0.0147   1.0000   1.0000
   0.750   0.0895   0.01185   0.00404  -0.0144   1.0000   1.0000
   1.000   0.1108   0.01214   0.00430  -0.0140   1.0000   1.0000
   1.250   0.1320   0.01245   0.00462  -0.0138   1.0000   1.0000
   1.500   0.1530   0.01280   0.00500  -0.0135   1.0000   1.0000
   1.750   0.1737   0.01318   0.00542  -0.0133   1.0000   1.0000
   2.000   0.2124   0.01373   0.00607  -0.0166   0.9930   1.0000
   2.250   0.2575   0.01430   0.00679  -0.0209   0.9831   1.0000
   2.500   0.3021   0.01479   0.00749  -0.0251   0.9717   1.0000
   2.750   0.4625   0.01150   0.00511  -0.0401   0.8195   1.0000
   3.000   0.4558   0.01470   0.00481  -0.0303   0.1171   1.0000
   3.250   0.4769   0.01619   0.00615  -0.0288   0.0868   1.0000
   3.500   0.4982   0.01762   0.00752  -0.0275   0.0741   1.0000
   3.750   0.5225   0.01884   0.00885  -0.0266   0.0645   1.0000
   4.000   0.5482   0.02129   0.01116  -0.0259   0.0613   1.0000
   4.250   0.5769   0.02347   0.01349  -0.0252   0.0609   1.0000
   4.500   0.6060   0.02551   0.01582  -0.0244   0.0623   1.0000
   4.750   0.6324   0.02805   0.01879  -0.0234   0.0597   1.0000
   5.000   0.6587   0.03165   0.02264  -0.0227   0.0617   1.0000
   5.250   0.6898   0.03625   0.02800  -0.0206   0.0871   1.0000
   6.500   0.7938   0.05675   0.05166  -0.0162   0.1461   1.0000
   7.750   0.8258   0.07803   0.07329  -0.0155   0.0865   1.0000
   8.000   0.8120   0.08156   0.07713  -0.0184   0.0836   1.0000
   8.250   0.8044   0.08599   0.08163  -0.0206   0.0806   1.0000
   8.500   0.7072   0.08599   0.08194  -0.0205   0.0983   1.0000
   8.750   0.6939   0.09187   0.08778  -0.0246   0.0979   1.0000
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