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NACA 16-012 (naca16012-il)

NACA 16-012 - NACA 16-012 airfoil


Airfoil naca16012-il
Details Dat file Parser  
(naca16012-il) NACA 16-012
NACA 16-012 airfoil
Max thickness 12% 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 16-012
1.0000     0.00120
0.9500     0.01415
0.9000     0.02517
0.8000     0.04199
0.7000     0.05269
0.6000     0.05835
0.5000     0.06000
0.4000     0.05855
0.3000     0.05417
0.2000     0.04664
0.1500     0.04135
0.1000     0.03457
0.0750     0.03032
0.0500     0.02509
0.0250     0.01805
0.0125     0.01292
0.0000     0.00000
0.0125     -0.01292
0.0250     -0.01805
0.0500     -0.02509
0.0750     -0.03032
0.1000     -0.03457
0.1500     -0.04135
0.2000     -0.04664
0.3000     -0.05417
0.4000     -0.05855
0.5000     -0.06000
0.6000     -0.05835
0.7000     -0.05269
0.8000     -0.04199
0.9000     -0.02517
0.9500     -0.01415
1.0000     -0.00120
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Polars for NACA 16-012 (naca16012-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca16012-il50,000921.1 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16012-il50,000522.1 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16012-il100,000928.2 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16012-il100,000530.8 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16012-il200,000944.9 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16012-il200,000532.5 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16012-il500,000942.5 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16012-il500,000544.5 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16012-il1,000,000951.7 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16012-il1,000,000555.7 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
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