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NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-210 (naca64210-il)
Reynolds number: 500,000
Max Cl/Cd: 76.28 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64210-il-500000.txt
Download as CSV file: xf-naca64210-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5584   0.08391   0.08163  -0.0289   1.0000   0.0222
  -9.750  -0.5710   0.07522   0.07290  -0.0366   1.0000   0.0222
  -9.500  -0.5877   0.06939   0.06699  -0.0412   1.0000   0.0222
  -9.250  -0.6052   0.06521   0.06273  -0.0433   1.0000   0.0222
  -9.000  -0.6203   0.06183   0.05926  -0.0431   1.0000   0.0222
  -8.750  -0.6297   0.05793   0.05519  -0.0431   1.0000   0.0222
  -8.500  -0.6354   0.05395   0.05099  -0.0427   1.0000   0.0223
  -8.250  -0.6575   0.04491   0.04165  -0.0423   1.0000   0.0229
  -8.000  -0.6510   0.04149   0.03815  -0.0417   1.0000   0.0235
  -7.750  -0.6402   0.03915   0.03571  -0.0408   1.0000   0.0240
  -7.500  -0.6295   0.03704   0.03349  -0.0395   1.0000   0.0246
  -7.250  -0.6204   0.03477   0.03105  -0.0377   1.0000   0.0253
  -7.000  -0.6218   0.02619   0.02162  -0.0336   0.9989   0.0192
  -6.750  -0.5892   0.02315   0.01817  -0.0355   0.9950   0.0200
  -6.500  -0.5574   0.02018   0.01481  -0.0368   0.9907   0.0202
  -6.250  -0.5233   0.01823   0.01259  -0.0384   0.9867   0.0208
  -6.000  -0.4875   0.01686   0.01102  -0.0403   0.9837   0.0216
  -5.750  -0.4544   0.01552   0.00951  -0.0416   0.9784   0.0227
  -5.500  -0.4223   0.01387   0.00781  -0.0430   0.9729   0.0243
  -5.250  -0.3890   0.01306   0.00696  -0.0444   0.9667   0.0256
  -5.000  -0.3576   0.01236   0.00621  -0.0453   0.9584   0.0272
  -4.750  -0.3286   0.01182   0.00561  -0.0456   0.9486   0.0290
  -4.500  -0.3008   0.01138   0.00510  -0.0456   0.9385   0.0308
  -4.250  -0.2768   0.01052   0.00417  -0.0451   0.9273   0.0344
  -4.000  -0.2515   0.01016   0.00375  -0.0445   0.9159   0.0379
  -3.750  -0.2258   0.00980   0.00331  -0.0441   0.9053   0.0425
  -3.500  -0.2001   0.00945   0.00294  -0.0437   0.8954   0.0518
  -3.250  -0.1747   0.00892   0.00254  -0.0433   0.8851   0.0921
  -3.000  -0.1533   0.00728   0.00202  -0.0433   0.8743   0.3822
  -2.750  -0.1286   0.00671   0.00193  -0.0430   0.8649   0.5336
  -2.500  -0.1020   0.00658   0.00187  -0.0427   0.8557   0.5813
  -2.250  -0.0748   0.00650   0.00182  -0.0425   0.8459   0.6115
  -2.000  -0.0475   0.00646   0.00177  -0.0422   0.8368   0.6317
  -1.750  -0.0204   0.00643   0.00175  -0.0420   0.8273   0.6574
  -1.500   0.0063   0.00641   0.00180  -0.0416   0.8180   0.6920
  -1.250   0.0334   0.00644   0.00182  -0.0412   0.8095   0.7145
  -1.000   0.0611   0.00644   0.00180  -0.0411   0.8000   0.7268
  -0.750   0.0887   0.00643   0.00179  -0.0410   0.7911   0.7364
  -0.500   0.1165   0.00644   0.00176  -0.0409   0.7824   0.7454
  -0.250   0.1445   0.00644   0.00175  -0.0409   0.7729   0.7550
   0.000   0.1722   0.00645   0.00176  -0.0408   0.7647   0.7639
   0.250   0.2001   0.00646   0.00177  -0.0408   0.7558   0.7734
   0.500   0.2279   0.00648   0.00179  -0.0407   0.7472   0.7830
   0.750   0.2555   0.00650   0.00182  -0.0406   0.7389   0.7923
   1.000   0.2834   0.00652   0.00186  -0.0405   0.7300   0.8025
   1.250   0.3108   0.00656   0.00191  -0.0404   0.7214   0.8126
   1.500   0.3380   0.00658   0.00196  -0.0402   0.7112   0.8221
   1.750   0.3655   0.00661   0.00202  -0.0400   0.7011   0.8322
   2.000   0.3922   0.00664   0.00205  -0.0396   0.6851   0.8429
   2.250   0.4176   0.00667   0.00205  -0.0389   0.6591   0.8532
   2.500   0.4432   0.00673   0.00208  -0.0383   0.6361   0.8639
   2.750   0.4693   0.00679   0.00214  -0.0379   0.6154   0.8750
   3.000   0.4949   0.00688   0.00223  -0.0373   0.5943   0.8865
   3.250   0.5197   0.00696   0.00233  -0.0365   0.5707   0.8981
   3.500   0.5431   0.00712   0.00242  -0.0355   0.5340   0.9107
   3.750   0.5642   0.00746   0.00253  -0.0341   0.4634   0.9248
   4.000   0.5772   0.00872   0.00297  -0.0318   0.2657   0.9430
   4.250   0.5939   0.01008   0.00356  -0.0304   0.0954   0.9648
   4.500   0.6260   0.01084   0.00407  -0.0318   0.0482   0.9900
   4.750   0.6539   0.01130   0.00453  -0.0322   0.0393   1.0000
   5.000   0.6788   0.01200   0.00526  -0.0320   0.0331   1.0000
   5.250   0.7049   0.01247   0.00576  -0.0319   0.0302   1.0000
   5.500   0.7299   0.01305   0.00636  -0.0317   0.0277   1.0000
   5.750   0.7507   0.01422   0.00757  -0.0308   0.0252   1.0000
   6.000   0.7750   0.01489   0.00830  -0.0304   0.0239   1.0000
   6.250   0.7992   0.01558   0.00904  -0.0299   0.0228   1.0000
   6.500   0.8228   0.01640   0.00992  -0.0294   0.0218   1.0000
   6.750   0.8464   0.01729   0.01086  -0.0288   0.0210   1.0000
   7.000   0.8701   0.01822   0.01185  -0.0283   0.0202   1.0000
   7.250   0.8935   0.01931   0.01300  -0.0278   0.0195   1.0000
   7.500   0.9161   0.02099   0.01474  -0.0273   0.0187   1.0000
   7.750   0.9378   0.02366   0.01763  -0.0266   0.0178   1.0000
   8.000   0.9606   0.02499   0.01915  -0.0260   0.0175   1.0000
   8.250   0.9817   0.02691   0.02132  -0.0251   0.0172   1.0000
   8.500   1.0006   0.02930   0.02400  -0.0240   0.0169   1.0000
   8.750   1.0154   0.03257   0.02764  -0.0225   0.0168   1.0000
   9.000   1.0252   0.03635   0.03183  -0.0206   0.0169   1.0000
   9.250   1.0318   0.04010   0.03596  -0.0185   0.0166   1.0000
   9.500   1.0305   0.04469   0.04092  -0.0161   0.0169   1.0000
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