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NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A210 (naca64a210-il)
Reynolds number: 200,000
Max Cl/Cd: 65.18 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a210-il-200000.txt
Download as CSV file: xf-naca64a210-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4297   0.10886   0.10540  -0.0247   1.0000   0.0494
 -10.750  -0.4401   0.10417   0.10075  -0.0286   1.0000   0.0500
 -10.500  -0.4482   0.09925   0.09585  -0.0318   1.0000   0.0502
 -10.250  -0.4562   0.09390   0.09052  -0.0352   1.0000   0.0503
 -10.000  -0.4524   0.08844   0.08510  -0.0325   1.0000   0.0518
  -9.750  -0.4427   0.08588   0.08254  -0.0307   1.0000   0.0533
  -9.500  -0.4420   0.08205   0.07872  -0.0313   1.0000   0.0546
  -9.250  -0.4456   0.07756   0.07425  -0.0327   1.0000   0.0559
  -9.000  -0.4529   0.07243   0.06916  -0.0350   1.0000   0.0571
  -8.750  -0.4652   0.06646   0.06322  -0.0385   1.0000   0.0579
  -8.500  -0.4877   0.05957   0.05635  -0.0442   1.0000   0.0575
  -8.250  -0.5113   0.05486   0.05160  -0.0458   1.0000   0.0573
  -8.000  -0.5272   0.05062   0.04729  -0.0456   1.0000   0.0582
  -7.750  -0.5416   0.04683   0.04341  -0.0441   1.0000   0.0596
  -7.500  -0.5662   0.04523   0.04140  -0.0401   1.0000   0.0626
  -7.250  -0.5777   0.04430   0.04013  -0.0358   1.0000   0.0632
  -7.000  -0.6037   0.04803   0.04344  -0.0374   1.0000   0.0649
  -6.750  -0.5953   0.04518   0.04067  -0.0357   1.0000   0.0666
  -6.500  -0.5878   0.04302   0.03845  -0.0336   1.0000   0.0692
  -6.250  -0.5698   0.02963   0.02533  -0.0284   1.0000   0.0735
  -6.000  -0.5689   0.02654   0.02189  -0.0262   1.0000   0.0793
  -5.750  -0.5477   0.02375   0.01906  -0.0267   0.9981   0.0837
  -5.500  -0.5400   0.02841   0.02198  -0.0238   1.0000   0.0473
  -5.250  -0.5186   0.02415   0.01698  -0.0220   1.0000   0.0410
  -5.000  -0.4950   0.02225   0.01473  -0.0210   0.9998   0.0403
  -4.750  -0.4586   0.02032   0.01261  -0.0229   0.9970   0.0413
  -4.500  -0.4207   0.01923   0.01143  -0.0252   0.9939   0.0450
  -4.250  -0.3846   0.01793   0.01000  -0.0268   0.9901   0.0469
  -4.000  -0.3470   0.01690   0.00886  -0.0288   0.9863   0.0495
  -3.750  -0.3095   0.01561   0.00762  -0.0313   0.9834   0.0555
  -3.500  -0.2752   0.01496   0.00691  -0.0328   0.9775   0.0635
  -3.250  -0.2382   0.01389   0.00594  -0.0352   0.9730   0.0853
  -3.000  -0.2080   0.01111   0.00527  -0.0375   0.9704   0.5450
  -2.750  -0.1786   0.01090   0.00539  -0.0375   0.9630   0.6545
  -2.500  -0.1421   0.01089   0.00544  -0.0390   0.9580   0.7085
  -2.250  -0.1085   0.01090   0.00547  -0.0398   0.9523   0.7436
  -2.000  -0.0765   0.01091   0.00551  -0.0401   0.9458   0.7792
  -1.750  -0.0441   0.01088   0.00560  -0.0401   0.9417   0.8180
  -1.500  -0.0185   0.01083   0.00554  -0.0392   0.9328   0.8398
  -1.250   0.0157   0.01070   0.00540  -0.0401   0.9280   0.8545
  -1.000   0.0427   0.01063   0.00532  -0.0397   0.9194   0.8689
  -0.750   0.0747   0.01050   0.00518  -0.0402   0.9138   0.8829
  -0.500   0.1014   0.01045   0.00512  -0.0397   0.9051   0.8978
  -0.250   0.1334   0.01035   0.00501  -0.0401   0.8993   0.9124
   0.000   0.1639   0.01032   0.00498  -0.0404   0.8907   0.9277
   0.250   0.2004   0.01024   0.00489  -0.0419   0.8849   0.9417
   0.500   0.2376   0.01022   0.00488  -0.0438   0.8768   0.9558
   0.750   0.2795   0.01015   0.00479  -0.0466   0.8706   0.9671
   1.000   0.3225   0.01012   0.00478  -0.0499   0.8623   0.9779
   1.250   0.3668   0.01002   0.00469  -0.0534   0.8557   0.9877
   1.500   0.4114   0.00998   0.00468  -0.0572   0.8464   0.9985
   1.750   0.4354   0.00994   0.00466  -0.0569   0.8365   1.0000
   2.000   0.4572   0.00992   0.00463  -0.0559   0.8264   1.0000
   2.250   0.4791   0.00994   0.00465  -0.0548   0.8141   1.0000
   2.500   0.5019   0.00993   0.00463  -0.0537   0.8007   1.0000
   2.750   0.5244   0.00978   0.00445  -0.0520   0.7817   1.0000
   3.000   0.5459   0.00962   0.00421  -0.0500   0.7550   1.0000
   3.250   0.5681   0.00959   0.00415  -0.0484   0.7288   1.0000
   3.500   0.5911   0.00963   0.00416  -0.0470   0.7030   1.0000
   3.750   0.6142   0.00970   0.00421  -0.0457   0.6741   1.0000
   4.000   0.6364   0.00982   0.00425  -0.0443   0.6360   1.0000
   4.250   0.6564   0.01007   0.00431  -0.0423   0.5727   1.0000
   4.500   0.6677   0.01099   0.00447  -0.0390   0.4035   1.0000
   4.750   0.6655   0.01384   0.00564  -0.0349   0.1116   1.0000
   5.000   0.6814   0.01520   0.00673  -0.0329   0.0696   1.0000
   5.250   0.7005   0.01619   0.00769  -0.0315   0.0568   1.0000
   5.500   0.7192   0.01728   0.00874  -0.0300   0.0501   1.0000
   5.750   0.7387   0.01849   0.00999  -0.0286   0.0468   1.0000
   6.000   0.7607   0.01959   0.01117  -0.0275   0.0441   1.0000
   6.250   0.7834   0.02064   0.01223  -0.0266   0.0409   1.0000
   6.500   0.8064   0.02252   0.01407  -0.0260   0.0382   1.0000
   6.750   0.8322   0.02484   0.01652  -0.0255   0.0372   1.0000
   7.000   0.8573   0.02661   0.01851  -0.0248   0.0367   1.0000
   7.250   0.8814   0.02898   0.02118  -0.0240   0.0366   1.0000
   7.500   0.9032   0.03156   0.02408  -0.0229   0.0365   1.0000
   7.750   0.9230   0.03361   0.02649  -0.0215   0.0355   1.0000
   8.000   0.9394   0.03715   0.03040  -0.0199   0.0361   1.0000
   8.750   0.9534   0.05644   0.05191  -0.0093   0.0668   1.0000
   9.000   0.9602   0.05955   0.05513  -0.0081   0.0645   1.0000
  12.500   0.6280   0.12848   0.12517  -0.0174   0.0598   1.0000
  12.750   0.6118   0.13351   0.13018  -0.0212   0.0576   1.0000
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