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NACA 65(2)-415 (naca652415-il)

NACA 65(2)-415 - NACA 65(2)-415 airfoil


Airfoil naca652415-il
Details Dat file Parser  
(naca652415-il) NACA 65(2)-415
NACA 65(2)-415 airfoil
Max thickness 15% at 39.9% chord.
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 65(2)-415
1.00000     0.00000
0.95040     0.01058
0.90080     0.02175
0.85109     0.03320
0.80126     0.04447
0.75131     0.05532
0.70124     0.06542
0.65106     0.07462
0.60079     0.08260
0.55043     0.08910
0.50000     0.09371
0.44953     0.09617
0.39903     0.09639
0.34854     0.09455
0.29807     0.09093
0.24764     0.08550
0.19726     0.07809
0.14697     0.06842
0.09682     0.05578
0.07184     0.04794
0.04697     0.03863
0.02231     0.02680
0.01016     0.01900
0.00542     0.01480
0.00313     0.01208
0.00000     0.00000
0.00687     -0.01008
0.00958     -0.01200
0.01484     -0.01472
0.02769     -0.01936
0.05303     -0.02599
0.07816     -0.03098
0.10318     -0.03510
0.15303     -0.04150
0.20274     -0.04625
0.25236     -0.04970
0.30193     -0.05205
0.35146     -0.05335
0.40097     -0.05355
0.45047     -0.05237
0.50000     -0.04962
0.54957     -0.04530
0.59921     -0.03976
0.64894     -0.03342
0.69876     -0.02654
0.74869     -0.01952
0.79874     -0.01263
0.84891     -0.00628
0.89920     -0.00107
0.94960     0.00206
1.00000     0.00000
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Selig format dat file

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Polars for NACA 65(2)-415 (naca652415-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca652415-il50,000923.9 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   naca652415-il50,000524 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca652415-il100,000946.7 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca652415-il100,000546.6 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca652415-il200,000970.8 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca652415-il200,000568 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca652415-il500,0009100.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca652415-il500,000591.1 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca652415-il1,000,0009120.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca652415-il1,000,0005105.9 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
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