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NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-206 (naca63206-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.34 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca63206-il-1000000.txt
Download as CSV file: xf-naca63206-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-206                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5608   0.07767   0.07613  -0.0117   1.0000   0.0049
  -7.750  -0.5664   0.07206   0.07056  -0.0175   1.0000   0.0051
  -7.500  -0.5611   0.06632   0.06477  -0.0238   1.0000   0.0050
  -7.250  -0.5561   0.06056   0.05894  -0.0283   1.0000   0.0051
  -7.000  -0.5478   0.05537   0.05366  -0.0315   1.0000   0.0052
  -6.750  -0.5364   0.05095   0.04913  -0.0337   1.0000   0.0054
  -6.500  -0.5226   0.04752   0.04560  -0.0351   1.0000   0.0057
  -6.250  -0.5065   0.04403   0.04198  -0.0362   1.0000   0.0061
  -6.000  -0.4884   0.04034   0.03813  -0.0370   1.0000   0.0070
  -4.000  -0.3055   0.01329   0.00878  -0.0340   0.9987   0.0082
  -3.750  -0.2719   0.01082   0.00601  -0.0350   0.9967   0.0081
  -3.250  -0.2050   0.00831   0.00322  -0.0376   0.9910   0.0112
  -3.000  -0.1708   0.00783   0.00271  -0.0391   0.9872   0.0129
  -2.750  -0.1357   0.00746   0.00230  -0.0407   0.9837   0.0158
  -2.500  -0.1023   0.00725   0.00208  -0.0420   0.9780   0.0172
  -2.250  -0.0690   0.00670   0.00139  -0.0432   0.9708   0.0208
  -2.000  -0.0375   0.00637   0.00107  -0.0439   0.9612   0.0411
  -1.750  -0.0087   0.00537   0.00083  -0.0448   0.9494   0.2793
  -1.500   0.0179   0.00455   0.00071  -0.0450   0.9358   0.5087
  -1.250   0.0441   0.00422   0.00067  -0.0448   0.9217   0.6174
  -1.000   0.0699   0.00400   0.00067  -0.0443   0.9076   0.7027
  -0.750   0.0959   0.00389   0.00067  -0.0437   0.8936   0.7564
  -0.500   0.1215   0.00381   0.00069  -0.0431   0.8794   0.8038
  -0.250   0.1475   0.00378   0.00069  -0.0425   0.8650   0.8322
   0.000   0.1735   0.00378   0.00070  -0.0420   0.8493   0.8532
   0.250   0.1993   0.00379   0.00070  -0.0414   0.8322   0.8737
   0.500   0.2251   0.00381   0.00072  -0.0408   0.8144   0.8914
   0.750   0.2503   0.00384   0.00074  -0.0400   0.7953   0.9090
   1.000   0.2749   0.00389   0.00075  -0.0391   0.7700   0.9277
   1.250   0.2980   0.00398   0.00074  -0.0379   0.7291   0.9483
   1.500   0.3247   0.00410   0.00073  -0.0375   0.6844   0.9734
   1.750   0.3550   0.00442   0.00077  -0.0382   0.6007   1.0000
   2.000   0.3816   0.00475   0.00086  -0.0381   0.5315   1.0000
   2.250   0.4066   0.00541   0.00102  -0.0379   0.3981   1.0000
   2.500   0.4288   0.00677   0.00140  -0.0377   0.1453   1.0000
   2.750   0.4542   0.00758   0.00175  -0.0376   0.0298   1.0000
   3.000   0.4814   0.00798   0.00217  -0.0374   0.0198   1.0000
   3.250   0.5088   0.00825   0.00249  -0.0374   0.0175   1.0000
   3.500   0.5359   0.00863   0.00292  -0.0373   0.0149   1.0000
   3.750   0.5624   0.00917   0.00352  -0.0370   0.0130   1.0000
   4.000   0.5862   0.01049   0.00501  -0.0363   0.0115   1.0000
   4.250   0.6125   0.01105   0.00562  -0.0360   0.0105   1.0000
   4.500   0.6389   0.01162   0.00624  -0.0357   0.0094   1.0000
   4.750   0.6648   0.01237   0.00709  -0.0354   0.0084   1.0000
   5.000   0.6906   0.01323   0.00802  -0.0350   0.0077   1.0000
   5.250   0.7165   0.01391   0.00877  -0.0348   0.0070   1.0000
   5.750   0.7640   0.01841   0.01379  -0.0332   0.0051   1.0000
   6.000   0.7846   0.02306   0.01898  -0.0315   0.0051   1.0000
   6.250   0.8023   0.03126   0.02790  -0.0282   0.0072   1.0000
   6.500   0.8206   0.03473   0.03164  -0.0272   0.0070   1.0000
   6.750   0.8372   0.03813   0.03528  -0.0265   0.0067   1.0000
   7.000   0.8520   0.04152   0.03888  -0.0259   0.0065   1.0000
   7.250   0.8635   0.04557   0.04316  -0.0252   0.0063   1.0000
   7.500   0.8710   0.05014   0.04799  -0.0248   0.0062   1.0000
   7.750   0.8708   0.05597   0.05405  -0.0245   0.0060   1.0000
   8.000   0.8625   0.06290   0.06116  -0.0247   0.0058   1.0000
   8.250   0.8171   0.05909   0.05765  -0.0235   0.0060   1.0000
   8.500   0.7984   0.06322   0.06184  -0.0230   0.0061   1.0000
   8.750   0.7758   0.06954   0.06823  -0.0266   0.0062   1.0000
   9.000   0.7515   0.08087   0.07960  -0.0358   0.0065   1.0000
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