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NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-209 (naca64209-il)
Reynolds number: 500,000
Max Cl/Cd: 60.75 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64209-il-500000-n5.txt
Download as CSV file: xf-naca64209-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6242   0.08163   0.07940  -0.0201   1.0000   0.0066
 -10.000  -0.6287   0.07632   0.07412  -0.0239   1.0000   0.0063
  -9.750  -0.6463   0.06681   0.06464  -0.0330   1.0000   0.0061
  -9.500  -0.6818   0.05853   0.05626  -0.0387   1.0000   0.0062
  -9.250  -0.7052   0.05137   0.04890  -0.0403   1.0000   0.0062
  -9.000  -0.7743   0.02898   0.02515  -0.0391   1.0000   0.0063
  -8.750  -0.7650   0.02460   0.02019  -0.0379   1.0000   0.0066
  -8.250  -0.7297   0.02073   0.01576  -0.0363   1.0000   0.0071
  -8.000  -0.7087   0.01982   0.01476  -0.0357   1.0000   0.0076
  -7.750  -0.6880   0.01868   0.01345  -0.0350   1.0000   0.0081
  -7.500  -0.6676   0.01742   0.01199  -0.0340   1.0000   0.0085
  -7.250  -0.6422   0.01620   0.01058  -0.0341   0.9972   0.0089
  -7.000  -0.6111   0.01514   0.00933  -0.0353   0.9911   0.0092
  -6.750  -0.5792   0.01420   0.00822  -0.0367   0.9852   0.0096
  -6.500  -0.5477   0.01348   0.00739  -0.0379   0.9779   0.0102
  -6.250  -0.5158   0.01290   0.00677  -0.0391   0.9701   0.0111
  -6.000  -0.4834   0.01243   0.00625  -0.0404   0.9623   0.0120
  -5.750  -0.4516   0.01228   0.00612  -0.0414   0.9529   0.0128
  -5.500  -0.4202   0.01244   0.00630  -0.0422   0.9430   0.0139
  -5.250  -0.3905   0.01247   0.00632  -0.0428   0.9321   0.0151
  -5.000  -0.3643   0.01172   0.00536  -0.0425   0.9204   0.0195
  -4.750  -0.3373   0.01158   0.00512  -0.0423   0.9087   0.0210
  -4.500  -0.3106   0.01143   0.00494  -0.0421   0.8973   0.0220
  -4.250  -0.2843   0.01118   0.00461  -0.0419   0.8863   0.0225
  -4.000  -0.2580   0.01094   0.00430  -0.0417   0.8756   0.0230
  -3.750  -0.2315   0.01074   0.00403  -0.0415   0.8650   0.0236
  -3.500  -0.2048   0.01053   0.00377  -0.0413   0.8544   0.0242
  -3.250  -0.1780   0.01036   0.00353  -0.0412   0.8444   0.0248
  -3.000  -0.1511   0.01019   0.00331  -0.0410   0.8346   0.0253
  -2.750  -0.1240   0.01004   0.00312  -0.0410   0.8246   0.0258
  -2.500  -0.0967   0.00997   0.00302  -0.0409   0.8151   0.0265
  -2.250  -0.0696   0.00984   0.00285  -0.0408   0.8055   0.0274
  -2.000  -0.0427   0.00945   0.00242  -0.0408   0.7956   0.0287
  -1.750  -0.0154   0.00923   0.00217  -0.0408   0.7866   0.0299
  -1.500   0.0120   0.00909   0.00199  -0.0408   0.7776   0.0302
  -1.250   0.0397   0.00896   0.00183  -0.0408   0.7680   0.0302
  -1.000   0.0673   0.00885   0.00169  -0.0408   0.7587   0.0302
  -0.750   0.0949   0.00876   0.00156  -0.0408   0.7493   0.0304
  -0.500   0.1228   0.00868   0.00146  -0.0408   0.7404   0.0306
  -0.250   0.1506   0.00862   0.00137  -0.0408   0.7319   0.0310
   0.000   0.1784   0.00857   0.00130  -0.0409   0.7227   0.0316
   0.250   0.2063   0.00852   0.00125  -0.0409   0.7138   0.0325
   0.500   0.2341   0.00850   0.00121  -0.0409   0.7051   0.0336
   0.750   0.2621   0.00847   0.00119  -0.0409   0.6967   0.0349
   1.000   0.2900   0.00847   0.00119  -0.0410   0.6880   0.0363
   1.250   0.3177   0.00848   0.00122  -0.0409   0.6770   0.0411
   1.500   0.3433   0.00709   0.00117  -0.0416   0.6597   0.5353
   1.750   0.3689   0.00686   0.00126  -0.0413   0.6321   0.6514
   2.250   0.4198   0.00712   0.00144  -0.0403   0.5374   0.7234
   2.500   0.4453   0.00733   0.00157  -0.0399   0.4891   0.7499
   2.750   0.4689   0.00781   0.00177  -0.0393   0.3919   0.7727
   3.000   0.4901   0.00879   0.00218  -0.0386   0.2412   0.7933
   3.250   0.5109   0.00949   0.00260  -0.0376   0.1338   0.8352
   3.500   0.5319   0.01006   0.00296  -0.0363   0.0628   0.8681
   3.750   0.5562   0.01040   0.00323  -0.0357   0.0399   0.8821
   4.000   0.5810   0.01062   0.00349  -0.0351   0.0330   0.8957
   4.250   0.6051   0.01089   0.00380  -0.0344   0.0275   0.9107
   4.500   0.6289   0.01112   0.00411  -0.0336   0.0244   0.9276
   4.750   0.6534   0.01136   0.00441  -0.0329   0.0218   0.9472
   5.000   0.6825   0.01170   0.00479  -0.0333   0.0193   0.9725
   5.250   0.7098   0.01234   0.00550  -0.0335   0.0171   1.0000
   5.500   0.7353   0.01284   0.00604  -0.0333   0.0164   1.0000
   5.750   0.7608   0.01330   0.00656  -0.0331   0.0157   1.0000
   6.000   0.7860   0.01379   0.00710  -0.0328   0.0148   1.0000
   6.250   0.8105   0.01439   0.00777  -0.0324   0.0142   1.0000
   6.500   0.8348   0.01502   0.00846  -0.0320   0.0136   1.0000
   6.750   0.8587   0.01568   0.00918  -0.0316   0.0131   1.0000
   7.000   0.8828   0.01630   0.00985  -0.0312   0.0125   1.0000
   7.250   0.9059   0.01710   0.01071  -0.0307   0.0117   1.0000
   7.500   0.9270   0.01837   0.01210  -0.0300   0.0110   1.0000
   7.750   0.9505   0.01917   0.01301  -0.0295   0.0107   1.0000
   8.000   0.9732   0.02015   0.01412  -0.0289   0.0103   1.0000
   8.250   0.9955   0.02124   0.01536  -0.0283   0.0098   1.0000
   8.500   1.0175   0.02232   0.01660  -0.0277   0.0093   1.0000
   8.750   1.0396   0.02317   0.01757  -0.0271   0.0087   1.0000
   9.000   1.0621   0.02365   0.01811  -0.0268   0.0082   1.0000
   9.250   1.0838   0.02425   0.01875  -0.0263   0.0078   1.0000
   9.500   1.1005   0.02599   0.02069  -0.0253   0.0074   1.0000
   9.750   1.1160   0.02799   0.02298  -0.0241   0.0071   1.0000
  10.000   1.1307   0.02995   0.02523  -0.0228   0.0069   1.0000
  10.250   1.1413   0.03247   0.02808  -0.0212   0.0065   1.0000
  10.500   1.1448   0.03582   0.03184  -0.0191   0.0062   1.0000
  10.750   1.1394   0.03993   0.03636  -0.0164   0.0059   1.0000
  11.000   1.1233   0.04406   0.04084  -0.0128   0.0058   1.0000
  11.250   1.0938   0.04923   0.04635  -0.0094   0.0057   1.0000
  11.500   1.0534   0.05647   0.05392  -0.0085   0.0057   1.0000
  11.750   1.0080   0.06589   0.06361  -0.0113   0.0057   1.0000
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