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NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-210 (naca65210-il)
Reynolds number: 50,000
Max Cl/Cd: 29.67 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65210-il-50000-n5.txt
Download as CSV file: xf-naca65210-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5343   0.11197   0.10475  -0.0225   1.0000   0.0765
 -10.250  -0.5388   0.10536   0.09820  -0.0270   1.0000   0.0638
 -10.000  -0.5328   0.10122   0.09407  -0.0274   1.0000   0.0611
  -9.750  -0.5340   0.09627   0.08918  -0.0298   1.0000   0.0586
  -9.250  -0.5823   0.08265   0.07562  -0.0434   1.0000   0.0519
  -8.750  -0.5843   0.07475   0.06769  -0.0436   1.0000   0.0507
  -8.500  -0.5896   0.07082   0.06371  -0.0438   1.0000   0.0501
  -8.250  -0.5943   0.06699   0.05977  -0.0437   1.0000   0.0496
  -8.000  -0.5978   0.06319   0.05582  -0.0432   1.0000   0.0490
  -7.750  -0.5991   0.05954   0.05198  -0.0423   1.0000   0.0486
  -7.500  -0.5985   0.05599   0.04818  -0.0411   1.0000   0.0482
  -7.250  -0.5960   0.05255   0.04446  -0.0395   1.0000   0.0479
  -7.000  -0.5913   0.04936   0.04094  -0.0378   1.0000   0.0480
  -6.750  -0.5847   0.04643   0.03760  -0.0359   1.0000   0.0492
  -6.500  -0.5759   0.04381   0.03446  -0.0338   1.0000   0.0509
  -6.250  -0.5644   0.04139   0.03154  -0.0317   1.0000   0.0518
  -6.000  -0.5506   0.03891   0.02868  -0.0299   1.0000   0.0521
  -5.750  -0.5353   0.03625   0.02575  -0.0283   1.0000   0.0528
  -5.500  -0.5184   0.03404   0.02330  -0.0268   1.0000   0.0538
  -5.250  -0.5004   0.03221   0.02122  -0.0253   1.0000   0.0555
  -5.000  -0.4823   0.03077   0.01962  -0.0239   1.0000   0.0592
  -4.750  -0.4625   0.02944   0.01801  -0.0223   1.0000   0.0629
  -4.500  -0.4418   0.02820   0.01652  -0.0206   1.0000   0.0648
  -4.250  -0.4225   0.02691   0.01523  -0.0188   1.0000   0.0673
  -4.000  -0.4047   0.02594   0.01420  -0.0171   1.0000   0.0710
  -3.750  -0.3873   0.02522   0.01324  -0.0154   1.0000   0.0783
  -3.500  -0.3708   0.02430   0.01234  -0.0140   1.0000   0.0856
  -3.250  -0.3530   0.02354   0.01143  -0.0126   1.0000   0.0933
  -3.000  -0.3270   0.02253   0.01046  -0.0133   0.9964   0.1120
  -2.750  -0.3095   0.01928   0.00982  -0.0133   0.9910   0.5009
  -2.500  -0.2964   0.01964   0.01075  -0.0073   0.9831   0.7464
  -2.250  -0.2841   0.02055   0.01175  -0.0001   0.9760   0.8477
  -2.000  -0.2357   0.02149   0.01243   0.0005   0.9760   0.9255
  -1.750  -0.1930   0.02143   0.01202  -0.0032   0.9704   0.9357
  -1.500  -0.1466   0.02141   0.01166  -0.0077   0.9656   0.9443
  -1.250  -0.1035   0.02137   0.01139  -0.0118   0.9602   0.9535
  -1.000  -0.0569   0.02135   0.01114  -0.0165   0.9551   0.9614
  -0.750  -0.0081   0.02136   0.01098  -0.0217   0.9509   0.9687
  -0.500   0.0336   0.02133   0.01084  -0.0256   0.9445   0.9774
  -0.250   0.0794   0.02135   0.01076  -0.0302   0.9394   0.9857
   0.000   0.1243   0.02137   0.01072  -0.0347   0.9341   0.9942
   0.250   0.1580   0.02144   0.01076  -0.0372   0.9268   1.0000
   0.500   0.1832   0.02155   0.01086  -0.0379   0.9184   1.0000
   0.750   0.2092   0.02168   0.01099  -0.0387   0.9104   1.0000
   1.000   0.2277   0.02185   0.01117  -0.0381   0.9009   1.0000
   1.250   0.2582   0.02201   0.01137  -0.0395   0.8944   1.0000
   1.500   0.2722   0.02224   0.01164  -0.0379   0.8842   1.0000
   1.750   0.2944   0.02248   0.01191  -0.0377   0.8761   1.0000
   2.000   0.3174   0.02273   0.01223  -0.0375   0.8679   1.0000
   2.250   0.3369   0.02305   0.01261  -0.0367   0.8589   1.0000
   2.500   0.3671   0.02332   0.01302  -0.0377   0.8522   1.0000
   2.750   0.3861   0.02370   0.01350  -0.0368   0.8423   1.0000
   3.000   0.4172   0.02398   0.01394  -0.0377   0.8352   1.0000
   3.250   0.4407   0.02434   0.01445  -0.0373   0.8251   1.0000
   3.500   0.4649   0.02468   0.01502  -0.0370   0.8147   1.0000
   3.750   0.4957   0.02490   0.01549  -0.0375   0.8051   1.0000
   4.000   0.5271   0.02503   0.01592  -0.0378   0.7942   1.0000
   4.250   0.5706   0.02270   0.01395  -0.0348   0.7420   1.0000
   4.500   0.5924   0.02022   0.01134  -0.0274   0.6286   1.0000
   4.750   0.6037   0.02035   0.01015  -0.0214   0.3509   1.0000
   5.000   0.5999   0.02326   0.01150  -0.0176   0.1440   1.0000
   5.250   0.6111   0.02505   0.01290  -0.0157   0.1043   1.0000
   5.500   0.6263   0.02643   0.01420  -0.0142   0.0874   1.0000
   5.750   0.6434   0.02777   0.01566  -0.0127   0.0796   1.0000
   6.000   0.6631   0.02911   0.01707  -0.0115   0.0733   1.0000
   6.250   0.6879   0.03048   0.01857  -0.0109   0.0662   1.0000
   6.500   0.7171   0.03197   0.02016  -0.0107   0.0606   1.0000
   6.750   0.7528   0.03418   0.02237  -0.0114   0.0577   1.0000
   7.000   0.7846   0.03633   0.02494  -0.0114   0.0554   1.0000
   7.250   0.8105   0.03850   0.02749  -0.0110   0.0519   1.0000
   7.500   0.8334   0.04081   0.03005  -0.0105   0.0488   1.0000
   7.750   0.8550   0.04362   0.03319  -0.0098   0.0477   1.0000
   8.000   0.8733   0.04675   0.03667  -0.0090   0.0469   1.0000
   8.250   0.8883   0.05018   0.04047  -0.0079   0.0464   1.0000
   8.500   0.8997   0.05378   0.04446  -0.0066   0.0462   1.0000
   8.750   0.9075   0.05784   0.04892  -0.0053   0.0457   1.0000
   9.000   0.9086   0.06128   0.05280  -0.0034   0.0452   1.0000
   9.250   0.9055   0.06479   0.05676  -0.0015   0.0447   1.0000
   9.500   0.8984   0.06845   0.06077   0.0002   0.0442   1.0000
   9.750   0.8882   0.07219   0.06480   0.0017   0.0440   1.0000
  10.000   0.8723   0.07582   0.06863   0.0032   0.0439   1.0000
  10.250   0.8560   0.07981   0.07277   0.0036   0.0440   1.0000
  10.500   0.8401   0.08424   0.07732   0.0029   0.0442   1.0000
  10.750   0.8236   0.08929   0.08246   0.0011   0.0444   1.0000
  11.000   0.8086   0.09486   0.08810  -0.0017   0.0447   1.0000
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