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NACA 16-006 (naca16006-il)

NACA 16-006 - NACA 16-006 airfoil


Airfoil naca16006-il
Details Dat file Parser  
(naca16006-il) NACA 16-006
NACA 16-006 airfoil
Max thickness 6% 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 16-006
1.0000     0.00060
0.9500     0.00707
0.9000     0.01259
0.8000     0.02099
0.7000     0.02635
0.6000     0.02917
0.5000     0.03000
0.4000     0.02927
0.3000     0.02709
0.2000     0.02332
0.1500     0.02067
0.1000     0.01729
0.0750     0.01516
0.0500     0.01255
0.0250     0.00903
0.0125     0.00646
0.0000     0.00000
0.0125     -0.00646
0.0250     -0.00903
0.0500     -0.01255
0.0750     -0.01516
0.1000     -0.01729
0.1500     -0.02067
0.2000     -0.02332
0.3000     -0.02709
0.4000     -0.02927
0.5000     -0.03000
0.6000     -0.02917
0.7000     -0.02635
0.8000     -0.02099
0.9000     -0.01259
0.9500     -0.00707
1.0000     -0.00060
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Lednicer format dat file
Selig format dat file

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Polars for NACA 16-006 (naca16006-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca16006-il50,000916.4 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16006-il50,000516.4 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16006-il100,000920.6 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16006-il100,000521.7 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16006-il200,000925.6 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16006-il200,000533.4 at α=1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16006-il500,000941.2 at α=1.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16006-il500,000534 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16006-il1,000,000940.8 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16006-il1,000,000536.2 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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