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NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-210 (naca64210-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.73 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64210-il-1000000.txt
Download as CSV file: xf-naca64210-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-210                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4820   0.10340   0.10186  -0.0134   1.0000   0.0125
 -11.250  -0.4806   0.09944   0.09790  -0.0149   1.0000   0.0127
 -11.000  -0.6490   0.04728   0.04569  -0.0390   1.0000   0.0088
 -10.750  -0.6411   0.04610   0.04449  -0.0408   1.0000   0.0089
 -10.500  -0.6221   0.04768   0.04610  -0.0411   1.0000   0.0091
 -10.250  -0.6224   0.04558   0.04396  -0.0430   1.0000   0.0092
 -10.000  -0.7614   0.04400   0.04192  -0.0453   1.0000   0.0083
  -9.750  -0.7926   0.01828   0.01543  -0.0419   1.0000   0.0086
  -9.500  -0.7942   0.01441   0.01122  -0.0405   1.0000   0.0090
  -9.250  -0.7736   0.01419   0.01099  -0.0402   1.0000   0.0093
  -9.000  -0.7582   0.01274   0.00938  -0.0394   1.0000   0.0095
  -8.750  -0.7423   0.01125   0.00770  -0.0386   1.0000   0.0098
  -8.500  -0.7250   0.01006   0.00636  -0.0377   1.0000   0.0101
  -8.250  -0.7102   0.00854   0.00463  -0.0363   1.0000   0.0105
  -8.000  -0.6834   0.00710   0.00295  -0.0372   0.9961   0.0109
  -7.750  -0.6540   0.00597   0.00163  -0.0385   0.9907   0.0114
  -7.500  -0.6219   0.00543   0.00095  -0.0399   0.9850   0.0118
  -7.250  -0.6249   0.01435   0.00940  -0.0385   0.9868   0.0125
  -7.000  -0.5911   0.01370   0.00873  -0.0403   0.9825   0.0132
  -6.750  -0.5589   0.01320   0.00820  -0.0416   0.9749   0.0139
  -6.500  -0.5268   0.01255   0.00747  -0.0428   0.9668   0.0146
  -6.250  -0.4974   0.01193   0.00677  -0.0434   0.9559   0.0152
  -6.000  -0.4713   0.01149   0.00626  -0.0431   0.9428   0.0158
  -5.750  -0.4456   0.01121   0.00590  -0.0427   0.9300   0.0162
  -5.500  -0.4232   0.01020   0.00477  -0.0420   0.9173   0.0177
  -5.250  -0.3977   0.00986   0.00438  -0.0416   0.9061   0.0187
  -5.000  -0.3718   0.00957   0.00402  -0.0413   0.8954   0.0197
  -4.750  -0.3456   0.00930   0.00368  -0.0410   0.8849   0.0209
  -4.500  -0.3187   0.00909   0.00342  -0.0408   0.8747   0.0220
  -4.250  -0.2926   0.00862   0.00285  -0.0406   0.8649   0.0247
  -4.000  -0.2657   0.00841   0.00261  -0.0405   0.8553   0.0276
  -3.750  -0.2382   0.00826   0.00241  -0.0404   0.8459   0.0301
  -3.500  -0.2111   0.00797   0.00208  -0.0403   0.8369   0.0364
  -3.250  -0.1836   0.00780   0.00187  -0.0403   0.8274   0.0429
  -3.000  -0.1564   0.00747   0.00166  -0.0403   0.8181   0.0774
  -2.750  -0.1304   0.00678   0.00140  -0.0405   0.8091   0.2043
  -2.500  -0.1052   0.00578   0.00111  -0.0408   0.7998   0.4105
  -2.250  -0.0781   0.00542   0.00103  -0.0409   0.7912   0.5099
  -2.000  -0.0504   0.00530   0.00098  -0.0409   0.7824   0.5510
  -1.750  -0.0222   0.00522   0.00094  -0.0410   0.7734   0.5771
  -1.500   0.0059   0.00518   0.00090  -0.0410   0.7647   0.5970
  -1.250   0.0340   0.00513   0.00089  -0.0411   0.7554   0.6224
  -1.000   0.0619   0.00507   0.00090  -0.0411   0.7467   0.6557
  -0.750   0.0898   0.00506   0.00091  -0.0411   0.7382   0.6785
  -0.500   0.1182   0.00505   0.00091  -0.0412   0.7294   0.6899
  -0.250   0.1466   0.00506   0.00091  -0.0412   0.7212   0.7004
   0.000   0.1749   0.00507   0.00091  -0.0413   0.7123   0.7098
   0.250   0.2033   0.00508   0.00093  -0.0414   0.7039   0.7186
   0.500   0.2315   0.00511   0.00094  -0.0415   0.6952   0.7280
   0.750   0.2598   0.00512   0.00097  -0.0416   0.6854   0.7372
   1.000   0.2880   0.00514   0.00099  -0.0417   0.6755   0.7462
   1.250   0.3161   0.00519   0.00103  -0.0417   0.6640   0.7558
   1.500   0.3438   0.00523   0.00106  -0.0416   0.6446   0.7651
   1.750   0.3712   0.00532   0.00109  -0.0415   0.6207   0.7748
   2.000   0.3989   0.00540   0.00114  -0.0415   0.5983   0.7848
   2.250   0.4263   0.00549   0.00121  -0.0414   0.5767   0.7942
   2.500   0.4538   0.00559   0.00128  -0.0414   0.5547   0.8037
   2.750   0.4813   0.00570   0.00136  -0.0413   0.5322   0.8137
   3.000   0.5075   0.00592   0.00148  -0.0411   0.4870   0.8235
   3.250   0.5310   0.00656   0.00170  -0.0405   0.3730   0.8337
   3.500   0.5521   0.00759   0.00213  -0.0398   0.2228   0.8447
   3.750   0.5742   0.00844   0.00252  -0.0392   0.1103   0.8558
   4.000   0.5981   0.00900   0.00286  -0.0387   0.0520   0.8666
   4.250   0.6235   0.00931   0.00313  -0.0383   0.0380   0.8779
   4.500   0.6490   0.00955   0.00341  -0.0379   0.0319   0.8901
   4.750   0.6737   0.00985   0.00373  -0.0373   0.0268   0.9031
   5.000   0.6979   0.01014   0.00411  -0.0366   0.0237   0.9169
   5.250   0.7215   0.01036   0.00438  -0.0357   0.0216   0.9322
   5.500   0.7433   0.01065   0.00471  -0.0345   0.0194   0.9520
   5.750   0.7700   0.01119   0.00535  -0.0344   0.0177   0.9831
   6.000   0.7981   0.01154   0.00574  -0.0348   0.0170   1.0000
   6.250   0.8240   0.01197   0.00621  -0.0346   0.0161   1.0000
   6.500   0.8494   0.01243   0.00670  -0.0344   0.0154   1.0000
   6.750   0.8744   0.01292   0.00721  -0.0341   0.0148   1.0000
   7.000   0.8986   0.01349   0.00781  -0.0337   0.0142   1.0000
   7.250   0.9171   0.01493   0.00935  -0.0325   0.0132   1.0000
   7.500   0.9411   0.01554   0.01002  -0.0321   0.0128   1.0000
   7.750   0.9650   0.01616   0.01070  -0.0316   0.0125   1.0000
   8.000   0.9882   0.01691   0.01152  -0.0311   0.0121   1.0000
   8.250   1.0108   0.01776   0.01246  -0.0304   0.0117   1.0000
   8.500   1.0332   0.01864   0.01342  -0.0298   0.0114   1.0000
   8.750   1.0553   0.01955   0.01441  -0.0292   0.0110   1.0000
   9.000   1.0776   0.02029   0.01523  -0.0286   0.0106   1.0000
   9.250   1.0999   0.02083   0.01579  -0.0282   0.0102   1.0000
   9.500   1.1200   0.02180   0.01683  -0.0274   0.0099   1.0000
   9.750   1.1282   0.02588   0.02129  -0.0254   0.0093   1.0000
  10.000   1.1478   0.02660   0.02215  -0.0245   0.0091   1.0000
  10.250   1.1649   0.02778   0.02349  -0.0234   0.0089   1.0000
  10.500   1.1791   0.02934   0.02523  -0.0220   0.0087   1.0000
  10.750   1.1888   0.03143   0.02756  -0.0202   0.0084   1.0000
  11.000   1.1933   0.03393   0.03032  -0.0180   0.0082   1.0000
  11.250   1.1895   0.03673   0.03338  -0.0149   0.0081   1.0000
  11.500   1.1801   0.03924   0.03611  -0.0112   0.0079   1.0000
  11.750   1.1675   0.04212   0.03920  -0.0082   0.0079   1.0000
  12.000   1.1399   0.04697   0.04435  -0.0057   0.0078   1.0000
  12.250   1.1232   0.05089   0.04845  -0.0050   0.0077   1.0000
  12.500   1.0678   0.06087   0.05880  -0.0067   0.0079   1.0000
  12.750   1.0312   0.06962   0.06778  -0.0107   0.0079   1.0000
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