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NACA 16-015 (naca16015-il)

NACA 16-015 - NACA 16-015 airfoil


Airfoil naca16015-il
Details Dat file Parser  
(naca16015-il) NACA 16-015
NACA 16-015 airfoil
Max thickness 15% at 50% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 16-015
1.0000     0.00150
0.9500     0.01768
0.9000     0.03147
0.8000     0.05248
0.7000     0.06587
0.6000     0.07293
0.5000     0.07500
0.4000     0.07318
0.3000     0.06772
0.2000     0.05830
0.1500     0.05168
0.1000     0.04322
0.0750     0.03790
0.0500     0.03137
0.0250     0.02257
0.0125     0.01615
0.0000     0.00000
0.0125     -0.01615
0.0250     -0.02257
0.0500     -0.03137
0.0750     -0.03790
0.1000     -0.04322
0.1500     -0.05168
0.2000     -0.05830
0.3000     -0.06772
0.4000     -0.07318
0.5000     -0.07500
0.6000     -0.07293
0.7000     -0.06587
0.8000     -0.05248
0.9000     -0.03147
0.9500     -0.01768
1.0000     -0.00150
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Selig format dat file

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Polars for NACA 16-015 (naca16015-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca16015-il50,000922.4 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16015-il50,000521.7 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16015-il100,000929.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16015-il100,000528.1 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16015-il200,000940.4 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16015-il200,000532 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16015-il500,000944.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16015-il500,000539.7 at α=10.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16015-il1,000,000950.5 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16015-il1,000,000550.5 at α=10.75°Mach=0 Ncrit=5Xfoil predictionDetails
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