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NACA6409 9% (n6409-il)

NACA6409 9% - NACA 6409


Airfoil n6409-il
Details Dat file Parser  
(n6409-il) NACA6409 9%
NACA 6409
Max thickness 9% at 29.3% chord.
Max camber 6% at 39.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
  NACA6409 9%       
  1.00000  0.00000
  0.99732  0.00084
  0.98930  0.00333
  0.97603  0.00737
  0.95760  0.01284
  0.93423  0.01954
  0.90615  0.02724
  0.87357  0.03571
  0.83690  0.04464
  0.79647  0.05378
  0.75272  0.06283
  0.70608  0.07153
  0.65710  0.07961
  0.60627  0.08684
  0.55413  0.09302
  0.50132  0.09796
  0.44840  0.10152
  0.39590  0.10360
  0.34367  0.10352
  0.29315  0.10086
  0.24502  0.09584
  0.19988  0.08874
  0.15830  0.07992
  0.12080  0.06982
  0.08780  0.05889
  0.05968  0.04762
  0.03677  0.03646
  0.01920  0.02581
  0.00720  0.01603
  0.00080  0.00737
  0.00000  0.00000
  0.00467 -0.00573
  0.01467 -0.00956
  0.02973 -0.01157
  0.04970 -0.01192
  0.07428 -0.01080
  0.10317 -0.00844
  0.13607 -0.00513
  0.17257 -0.00119
  0.21235  0.00307
  0.25498  0.00729
  0.30012  0.01112
  0.34730  0.01425
  0.39618  0.01639
  0.44707  0.01772
  0.49868  0.01871
  0.55040  0.01925
  0.60167  0.01929
  0.65193  0.01880
  0.70065  0.01780
  0.74728  0.01634
  0.79130  0.01451
  0.83223  0.01241
  0.86957  0.01017
  0.90288  0.00791
  0.93180  0.00576
  0.95593  0.00383
  0.97503  0.00221
  0.98883  0.00101
  0.99722  0.00025
  1.00000  0.00000
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Polars for NACA6409 9% (n6409-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n6409-il50,000927.1 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n6409-il50,000536 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   n6409-il100,000961.6 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n6409-il100,000563.7 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   n6409-il200,000987.1 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   n6409-il200,000587.4 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   n6409-il500,0009122.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n6409-il500,0005118.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   n6409-il1,000,0009151 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   n6409-il1,000,0005144.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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