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NACA 0010 (naca0010-il)

NACA 0010 - NACA 0010 airfoil


Airfoil naca0010-il
Details Dat file Parser  
(naca0010-il) NACA 0010
NACA 0010 airfoil
Max thickness 10% at 30% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 0010
1.0000     0.00105
0.9500     0.00672
0.9000     0.01207
0.8000     0.02187
0.7000     0.03053
0.6000     0.03803
0.5000     0.04412
0.4000     0.04837
0.3000     0.05002
0.2500     0.04952
0.2000     0.04782
0.1500     0.04455
0.1000     0.03902
0.0750     0.03500
0.0500     0.02962
0.0250     0.02178
0.0125     0.01578
0.0000     0.00000
0.0125     -0.01578
0.0250     -0.02178
0.0500     -0.02962
0.0750     -0.03500
0.1000     -0.03902
0.1500     -0.04455
0.2000     -0.04782
0.2500     -0.04952
0.3000     -0.05002
0.4000     -0.04837
0.5000     -0.04412
0.6000     -0.03803
0.7000     -0.03053
0.8000     -0.02187
0.9000     -0.01207
0.9500     -0.00672
1.0000     -0.00105
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Lednicer format dat file
Selig format dat file

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Polars for NACA 0010 (naca0010-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca0010-il50,000925.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0010-il50,000525.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0010-il100,000935.8 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0010-il100,000533.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0010-il200,000944.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0010-il200,000542.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0010-il500,000955.2 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0010-il500,000557.8 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0010-il1,000,000970.2 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0010-il1,000,000574.1 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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