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NACA 0010-66 (naca001066-il)

NACA 0010-66 - NACA 0010-66 airfoil


Airfoil naca001066-il
Details Dat file Parser  
(naca001066-il) NACA 0010-66
NACA 0010-66 airfoil
Max thickness 10% at 60% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 0010-66
1.0000     0.00100
0.9500     0.01656
0.9000     0.02833
0.8000     0.04300
0.7000     0.04889
0.6000     0.05000
0.5000     0.04956
0.4000     0.04822
0.3000     0.04578
0.2000     0.04178
0.1500     0.03856
0.1000     0.03400
0.0750     0.03089
0.0500     0.02656
0.0250     0.02011
0.0125     0.01489
0.0000     0.00000
0.0125     -0.01489
0.0250     -0.02011
0.0500     -0.02656
0.0750     -0.03089
0.1000     -0.03400
0.1500     -0.03856
0.2000     -0.04178
0.3000     -0.04578
0.4000     -0.04822
0.5000     -0.04956
0.6000     -0.05000
0.7000     -0.04889
0.8000     -0.04300
0.9000     -0.02833
0.9500     -0.01656
1.0000     -0.00100
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Lednicer format dat file
Selig format dat file

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Polars for NACA 0010-66 (naca001066-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca001066-il50,000920.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001066-il50,000521.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001066-il100,000926.6 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001066-il100,000528.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001066-il200,000933.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001066-il200,000534.4 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001066-il500,000942.9 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001066-il500,000547.1 at α=10.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca001066-il1,000,000953.6 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca001066-il1,000,000559.7 at α=10.5°Mach=0 Ncrit=5Xfoil predictionDetails
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