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NACA 65-209 (naca65209-il)

NACA 65-209 - NACA 65-209 airfoil


Airfoil naca65209-il
Details Dat file Parser  
(naca65209-il) NACA 65-209
NACA 65-209 airfoil
Max thickness 9% at 40% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 65-209
1.00000     0.00000
0.95013     0.00596
0.90026     0.01255
0.85035     0.01933
0.80040     0.02601
0.75041     0.03237
0.70039     0.03828
0.65033     0.04358
0.60024     0.04814
0.55013     0.05181
0.50000     0.05439
0.44986     0.05564
0.39971     0.05567
0.34956     0.05461
0.29942     0.05254
0.24929     0.04944
0.19918     0.04522
0.14909     0.03971
0.09904     0.03251
0.07405     0.02805
0.04908     0.02275
0.02417     0.01605
0.01177     0.01162
0.00684     0.00912
0.00441     0.00748
0.00000     0.00000
0.00559     -0.00648
0.00816     -0.00772
0.01323     -0.00948
0.02583     -0.01233
0.05092     -0.01643
0.07595     -0.01957
0.10096     -0.02217
0.15091     -0.02625
0.20082     -0.02930
0.25071     -0.03154
0.30058     -0.03310
0.35044     -0.03401
0.40029     -0.03425
0.45014     -0.03374
0.50000     -0.03233
0.54987     -0.02991
0.59976     -0.02672
0.64967     -0.02298
0.69961     -0.01884
0.74959     -0.01447
0.79960     -0.01009
0.84965     -0.00587
0.89974     -0.00221
0.94987     0.00036
1.00000     0.00000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 65-209 (naca65209-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca65209-il50,000924.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65209-il50,000530.4 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65209-il100,000943.6 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65209-il100,000542.1 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65209-il200,000959.3 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65209-il200,000550.4 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65209-il500,000971.3 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65209-il500,000561.2 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca65209-il1,000,000980.6 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca65209-il1,000,000568 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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