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NACA 66-206 (naca66206-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 66-206 (naca66206-il)
Reynolds number: 50,000
Max Cl/Cd: 22.55 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca66206-il-50000-n5.txt
Download as CSV file: xf-naca66206-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-206                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5480   0.11102   0.10394  -0.0105   1.0000   0.0851
  -9.000  -0.5556   0.10869   0.10174  -0.0147   1.0000   0.0882
  -8.750  -0.5665   0.10617   0.09935  -0.0197   1.0000   0.0890
  -8.500  -0.5444   0.09999   0.09313  -0.0150   1.0000   0.0945
  -8.250  -0.5443   0.09672   0.08993  -0.0167   1.0000   0.0982
  -8.000  -0.5600   0.09428   0.08762  -0.0235   1.0000   0.1020
  -7.750  -0.5501   0.08945   0.08285  -0.0217   1.0000   0.1057
  -7.500  -0.5461   0.08581   0.07923  -0.0226   1.0000   0.1107
  -7.250  -0.5505   0.08225   0.07570  -0.0266   1.0000   0.1179
  -6.250  -0.5047   0.06362   0.05618  -0.0354   1.0000   0.0483
  -6.000  -0.4950   0.05914   0.05174  -0.0348   1.0000   0.0470
  -5.750  -0.4837   0.05540   0.04781  -0.0347   1.0000   0.0467
  -5.500  -0.4708   0.05177   0.04393  -0.0343   1.0000   0.0465
  -5.250  -0.4566   0.04819   0.04010  -0.0338   1.0000   0.0456
  -5.000  -0.4408   0.04469   0.03630  -0.0331   1.0000   0.0439
  -4.750  -0.4229   0.04135   0.03259  -0.0324   1.0000   0.0420
  -4.500  -0.4031   0.03813   0.02891  -0.0314   1.0000   0.0405
  -4.250  -0.3819   0.03519   0.02547  -0.0303   1.0000   0.0396
  -4.000  -0.3596   0.03248   0.02228  -0.0292   1.0000   0.0395
  -3.750  -0.3365   0.03006   0.01942  -0.0280   1.0000   0.0400
  -3.500  -0.3132   0.02812   0.01705  -0.0269   1.0000   0.0447
  -3.250  -0.2891   0.02624   0.01460  -0.0257   1.0000   0.0502
  -3.000  -0.2654   0.02439   0.01258  -0.0243   1.0000   0.0524
  -2.750  -0.2419   0.02293   0.01090  -0.0227   1.0000   0.0556
  -2.500  -0.2189   0.02178   0.00946  -0.0212   1.0000   0.0595
  -2.250  -0.1973   0.02070   0.00821  -0.0200   1.0000   0.0670
  -2.000  -0.1756   0.01981   0.00721  -0.0190   1.0000   0.0885
  -1.500  -0.1085   0.01550   0.00587  -0.0182   1.0000   1.0000
  -1.250  -0.0933   0.01547   0.00539  -0.0162   1.0000   1.0000
  -1.000  -0.0764   0.01548   0.00508  -0.0147   1.0000   1.0000
  -0.750  -0.0581   0.01551   0.00485  -0.0134   1.0000   1.0000
  -0.500  -0.0388   0.01557   0.00469  -0.0124   1.0000   1.0000
  -0.250  -0.0188   0.01565   0.00459  -0.0114   1.0000   1.0000
   0.000   0.0017   0.01576   0.00454  -0.0106   1.0000   1.0000
   0.250   0.0226   0.01589   0.00450  -0.0099   1.0000   1.0000
   0.500   0.0438   0.01605   0.00455  -0.0093   1.0000   1.0000
   0.750   0.0652   0.01622   0.00466  -0.0087   1.0000   1.0000
   1.000   0.0867   0.01642   0.00483  -0.0081   1.0000   1.0000
   1.250   0.1082   0.01665   0.00505  -0.0076   1.0000   1.0000
   1.500   0.1298   0.01689   0.00533  -0.0072   1.0000   1.0000
   1.750   0.1513   0.01716   0.00565  -0.0067   1.0000   1.0000
   2.000   0.1728   0.01746   0.00602  -0.0063   1.0000   1.0000
   2.250   0.1942   0.01778   0.00645  -0.0059   1.0000   1.0000
   2.500   0.2310   0.01830   0.00718  -0.0086   0.9915   1.0000
   2.750   0.2689   0.01885   0.00809  -0.0115   0.9824   1.0000
   3.000   0.3075   0.01938   0.00897  -0.0144   0.9722   1.0000
   3.250   0.3474   0.01991   0.00994  -0.0174   0.9601   1.0000
   3.500   0.4695   0.02082   0.00800  -0.0234   0.0932   1.0000
   3.750   0.4912   0.02215   0.00941  -0.0223   0.0740   1.0000
   4.000   0.5133   0.02364   0.01101  -0.0212   0.0658   1.0000
   4.250   0.5400   0.02514   0.01285  -0.0202   0.0606   1.0000
   4.500   0.5691   0.02707   0.01489  -0.0199   0.0514   1.0000
   4.750   0.5988   0.02898   0.01712  -0.0194   0.0444   1.0000
   5.000   0.6277   0.03159   0.02001  -0.0189   0.0421   1.0000
   5.250   0.6539   0.03485   0.02360  -0.0183   0.0406   1.0000
   5.500   0.6774   0.03869   0.02799  -0.0173   0.0400   1.0000
   5.750   0.6990   0.04150   0.03149  -0.0158   0.0389   1.0000
   6.000   0.7182   0.04440   0.03511  -0.0141   0.0357   1.0000
   6.250   0.7344   0.04788   0.03913  -0.0127   0.0337   1.0000
   6.500   0.7483   0.05182   0.04353  -0.0115   0.0340   1.0000
   6.750   0.7596   0.05595   0.04808  -0.0104   0.0346   1.0000
   7.000   0.7685   0.06021   0.05269  -0.0095   0.0353   1.0000
   7.250   0.7751   0.06454   0.05730  -0.0088   0.0362   1.0000
   7.500   0.7793   0.06901   0.06199  -0.0085   0.0372   1.0000
   7.750   0.7819   0.07357   0.06670  -0.0083   0.0382   1.0000
   8.000   0.7850   0.07784   0.07123  -0.0084   0.0423   1.0000
   8.250   0.7774   0.08283   0.07640  -0.0099   0.0451   1.0000
   8.500   0.7700   0.08753   0.08116  -0.0111   0.0474   1.0000
   8.750   0.7650   0.09213   0.08576  -0.0124   0.0497   1.0000
   9.000   0.6560   0.08801   0.08203  -0.0100   0.0439   1.0000
   9.250   0.6464   0.09407   0.08806  -0.0137   0.0456   1.0000
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