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NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-206 (naca64206-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.75 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64206-il-1000000.txt
Download as CSV file: xf-naca64206-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5409   0.08484   0.08325  -0.0098   1.0000   0.0049
  -8.000  -0.5408   0.08082   0.07925  -0.0121   1.0000   0.0049
  -7.750  -0.5443   0.07658   0.07504  -0.0150   1.0000   0.0049
  -7.500  -0.5409   0.07126   0.06971  -0.0216   1.0000   0.0049
  -7.250  -0.5348   0.06609   0.06451  -0.0261   1.0000   0.0049
  -7.000  -0.5270   0.06091   0.05926  -0.0295   1.0000   0.0049
  -6.750  -0.5305   0.05132   0.04949  -0.0342   1.0000   0.0052
  -6.500  -0.5193   0.04655   0.04458  -0.0357   1.0000   0.0054
  -6.250  -0.5049   0.04341   0.04132  -0.0365   1.0000   0.0057
  -6.000  -0.4885   0.03999   0.03775  -0.0369   1.0000   0.0059
  -5.750  -0.4704   0.03742   0.03503  -0.0370   1.0000   0.0070
  -4.000  -0.2983   0.01470   0.01034  -0.0358   0.9958   0.0087
  -3.750  -0.2645   0.01137   0.00663  -0.0367   0.9940   0.0081
  -3.500  -0.2323   0.01003   0.00514  -0.0375   0.9909   0.0090
  -3.250  -0.1996   0.00874   0.00369  -0.0387   0.9876   0.0106
  -3.000  -0.1654   0.00793   0.00281  -0.0402   0.9846   0.0124
  -2.750  -0.1304   0.00751   0.00236  -0.0419   0.9817   0.0148
  -2.500  -0.0994   0.00719   0.00199  -0.0426   0.9745   0.0173
  -2.250  -0.0660   0.00689   0.00164  -0.0439   0.9688   0.0186
  -2.000  -0.0359   0.00648   0.00114  -0.0443   0.9592   0.0283
  -1.750  -0.0072   0.00581   0.00090  -0.0448   0.9486   0.1685
  -1.500   0.0187   0.00467   0.00072  -0.0452   0.9366   0.4801
  -1.250   0.0449   0.00430   0.00067  -0.0450   0.9240   0.5973
  -1.000   0.0707   0.00403   0.00067  -0.0445   0.9113   0.6947
  -0.750   0.0966   0.00390   0.00067  -0.0440   0.8988   0.7552
  -0.500   0.1221   0.00380   0.00069  -0.0434   0.8860   0.8045
  -0.250   0.1478   0.00376   0.00070  -0.0427   0.8731   0.8383
   0.000   0.1731   0.00373   0.00072  -0.0420   0.8598   0.8671
   0.250   0.1990   0.00374   0.00073  -0.0414   0.8446   0.8846
   0.500   0.2246   0.00376   0.00074  -0.0408   0.8269   0.9004
   0.750   0.2497   0.00381   0.00075  -0.0400   0.8063   0.9164
   1.000   0.2735   0.00388   0.00074  -0.0389   0.7710   0.9328
   1.250   0.2967   0.00400   0.00073  -0.0377   0.7256   0.9516
   1.500   0.3237   0.00413   0.00073  -0.0375   0.6779   0.9732
   1.750   0.3553   0.00440   0.00078  -0.0384   0.6091   1.0000
   2.000   0.3815   0.00475   0.00087  -0.0383   0.5355   1.0000
   2.250   0.4036   0.00594   0.00114  -0.0379   0.2945   1.0000
   2.500   0.4269   0.00711   0.00150  -0.0377   0.0848   1.0000
   2.750   0.4533   0.00764   0.00180  -0.0376   0.0264   1.0000
   3.000   0.4807   0.00797   0.00217  -0.0375   0.0193   1.0000
   3.250   0.5079   0.00832   0.00257  -0.0374   0.0159   1.0000
   3.500   0.5345   0.00883   0.00314  -0.0372   0.0135   1.0000
   3.750   0.5594   0.00980   0.00425  -0.0367   0.0123   1.0000
   4.000   0.5845   0.01070   0.00524  -0.0362   0.0114   1.0000
   4.250   0.6114   0.01110   0.00568  -0.0360   0.0102   1.0000
   4.500   0.6376   0.01169   0.00632  -0.0358   0.0089   1.0000
   4.750   0.6634   0.01250   0.00723  -0.0354   0.0081   1.0000
   5.000   0.6891   0.01345   0.00827  -0.0350   0.0075   1.0000
   5.250   0.7145   0.01429   0.00917  -0.0348   0.0066   1.0000
   5.500   0.7375   0.01734   0.01260  -0.0337   0.0054   1.0000
   5.750   0.7606   0.02082   0.01649  -0.0323   0.0051   1.0000
   8.750   0.8051   0.08366   0.08223  -0.0297   0.0059   1.0000
   9.000   0.7973   0.09106   0.08962  -0.0369   0.0059   1.0000
   9.250   0.7947   0.09694   0.09548  -0.0410   0.0059   1.0000
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