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NACA 0015 (naca0015-il)

NACA 0015 - NACA 0015 airfoil


Airfoil naca0015-il
Details Dat file Parser  
(naca0015-il) NACA 0015
NACA 0015 airfoil
Max thickness 15% 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 0015
1.0000     0.00158
0.9500     0.01008
0.9000     0.01810
0.8000     0.03279
0.7000     0.04580
0.6000     0.05704
0.5000     0.06617
0.4000     0.07254
0.3000     0.07502
0.2500     0.07427
0.2000     0.07172
0.1500     0.06682
0.1000     0.05853
0.0750     0.05250
0.0500     0.04443
0.0250     0.03268
0.0125     0.02367
0.0000     0.00000
0.0125     -0.02367
0.0250     -0.03268
0.0500     -0.04443
0.0750     -0.05250
0.1000     -0.05853
0.1500     -0.06682
0.2000     -0.07172
0.2500     -0.07427
0.3000     -0.07502
0.4000     -0.07254
0.5000     -0.06617
0.6000     -0.05704
0.7000     -0.04580
0.8000     -0.03279
0.9000     -0.01810
0.9500     -0.01008
1.0000     -0.00158
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Lednicer format dat file
Selig format dat file

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Polars for NACA 0015 (naca0015-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca0015-il50,000924.7 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0015-il50,000526.9 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0015-il100,000937.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0015-il100,000537.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0015-il200,000949.6 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0015-il200,000548.6 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0015-il500,000966.4 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0015-il500,000563.2 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0015-il1,000,000977.9 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0015-il1,000,000575.1 at α=10.25°Mach=0 Ncrit=5Xfoil predictionDetails
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