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NACA 66-206 (naca66206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 66-206 (naca66206-il)
Reynolds number: 1,000,000
Max Cl/Cd: 76.29 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca66206-il-1000000.txt
Download as CSV file: xf-naca66206-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-206                                     
  
 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  -0.5159   0.08473   0.08311  -0.0204   1.0000   0.0053
  -8.000  -0.5171   0.08089   0.07929  -0.0227   1.0000   0.0054
  -7.750  -0.5220   0.07699   0.07541  -0.0261   1.0000   0.0054
  -7.500  -0.5195   0.07267   0.07108  -0.0294   1.0000   0.0054
  -7.250  -0.5160   0.06835   0.06673  -0.0318   1.0000   0.0054
  -7.000  -0.5112   0.06428   0.06261  -0.0333   1.0000   0.0054
  -6.750  -0.5063   0.06026   0.05853  -0.0340   1.0000   0.0054
  -6.500  -0.5034   0.05675   0.05496  -0.0333   1.0000   0.0054
  -6.250  -0.4937   0.05260   0.05071  -0.0337   0.9991   0.0054
  -6.000  -0.4670   0.04698   0.04492  -0.0377   0.9964   0.0054
  -5.750  -0.4391   0.04157   0.03930  -0.0409   0.9939   0.0054
  -5.500  -0.4129   0.03667   0.03416  -0.0429   0.9902   0.0054
  -5.250  -0.3902   0.02801   0.02500  -0.0457   0.9861   0.0064
  -5.000  -0.3554   0.03019   0.02727  -0.0468   0.9850   0.0107
  -3.750  -0.2087   0.01285   0.00817  -0.0498   0.9677   0.0089
  -3.500  -0.1832   0.01046   0.00552  -0.0487   0.9616   0.0084
  -3.250  -0.1564   0.00932   0.00426  -0.0483   0.9566   0.0096
  -3.000  -0.1287   0.00951   0.00443  -0.0483   0.9511   0.0110
  -2.750  -0.1055   0.00802   0.00279  -0.0474   0.9448   0.0126
  -2.500  -0.0796   0.00751   0.00223  -0.0471   0.9395   0.0154
  -2.250  -0.0532   0.00722   0.00187  -0.0467   0.9336   0.0187
  -2.000  -0.0265   0.00703   0.00161  -0.0465   0.9287   0.0203
  -1.750   0.0001   0.00673   0.00124  -0.0463   0.9230   0.0257
  -1.500   0.0263   0.00628   0.00102  -0.0461   0.9178   0.1093
  -1.250   0.0483   0.00474   0.00082  -0.0461   0.9124   0.5475
  -1.000   0.0719   0.00411   0.00084  -0.0454   0.9068   0.7515
  -0.750   0.0972   0.00400   0.00086  -0.0447   0.9020   0.8128
  -0.500   0.1222   0.00395   0.00091  -0.0439   0.8957   0.8517
  -0.250   0.1474   0.00395   0.00094  -0.0432   0.8890   0.8734
   0.000   0.1724   0.00395   0.00094  -0.0424   0.8782   0.8890
   0.250   0.1970   0.00396   0.00093  -0.0414   0.8646   0.9007
   0.500   0.2226   0.00396   0.00094  -0.0408   0.8532   0.9085
   0.750   0.2491   0.00398   0.00094  -0.0405   0.8418   0.9154
   1.000   0.2747   0.00399   0.00093  -0.0399   0.8262   0.9208
   1.250   0.2997   0.00406   0.00092  -0.0392   0.7967   0.9269
   1.500   0.3227   0.00423   0.00089  -0.0380   0.7342   0.9329
   1.750   0.3383   0.00523   0.00102  -0.0357   0.5017   0.9413
   2.000   0.3551   0.00629   0.00131  -0.0339   0.2753   0.9499
   2.250   0.3730   0.00737   0.00161  -0.0324   0.0541   0.9596
   2.500   0.3973   0.00771   0.00189  -0.0317   0.0252   0.9692
   2.750   0.4263   0.00791   0.00210  -0.0321   0.0188   0.9778
   3.000   0.4560   0.00881   0.00318  -0.0326   0.0145   0.9868
   3.250   0.4882   0.00928   0.00369  -0.0338   0.0139   0.9973
   3.500   0.5147   0.00977   0.00426  -0.0337   0.0135   1.0000
   3.750   0.5409   0.01018   0.00470  -0.0335   0.0122   1.0000
   4.000   0.5667   0.01071   0.00527  -0.0333   0.0101   1.0000
   4.250   0.5932   0.01105   0.00561  -0.0332   0.0086   1.0000
   4.500   0.6161   0.01263   0.00730  -0.0323   0.0076   1.0000
   4.750   0.6407   0.01433   0.00919  -0.0316   0.0065   1.0000
   5.000   0.6668   0.01561   0.01062  -0.0311   0.0054   1.0000
   5.250   0.6896   0.02002   0.01553  -0.0291   0.0055   1.0000
   6.500   0.7299   0.03418   0.03182  -0.0180   0.0069   1.0000
   6.750   0.7381   0.03900   0.03684  -0.0168   0.0069   1.0000
   7.000   0.7439   0.04400   0.04201  -0.0157   0.0069   1.0000
   7.250   0.7466   0.04913   0.04730  -0.0148   0.0069   1.0000
   7.500   0.7464   0.05422   0.05251  -0.0141   0.0069   1.0000
   7.750   0.7425   0.05916   0.05757  -0.0136   0.0069   1.0000
   8.000   0.7327   0.06381   0.06231  -0.0129   0.0069   1.0000
   8.250   0.7154   0.06775   0.06632  -0.0121   0.0069   1.0000
   8.500   0.6979   0.07282   0.07144  -0.0140   0.0069   1.0000
   8.750   0.6823   0.07967   0.07832  -0.0194   0.0069   1.0000
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