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NACA 23015 (naca23015-il)

NACA 23015 - NACA 23015 airfoil


Airfoil naca23015-il
Details Dat file Parser  
(naca23015-il) NACA 23015
NACA 23015 airfoil
Max thickness 15% at 30% chord.
Max camber 1.8% at 15% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 23015
1.0000     0.0016
0.9500     0.0112
0.9000     0.0204
0.8000     0.0373
0.7000     0.0525
0.6000     0.0661
0.5000     0.0774
0.4000     0.0859
0.3000     0.0905
0.2500     0.0908
0.2000     0.0892
0.1500     0.0852
0.1000     0.0764
0.0750     0.0690
0.0500     0.0589
0.0250     0.0444
0.0125     0.0334
0.0000     0.0000
0.0125     -0.0154
0.0250     -0.0225
0.0500     -0.0304
0.0750     -0.0361
0.1000     -0.0409
0.1500     -0.0484
0.2000     -0.0541
0.2500     -0.0578
0.3000     -0.0596
0.4000     -0.0592
0.5000     -0.0550
0.6000     -0.0481
0.7000     -0.0391
0.8000     -0.0283
0.9000     -0.0159
0.9500     -0.0090
1.0000     -0.0016

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Polars for NACA 23015 (naca23015-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca23015-il50,000921 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23015-il50,000527.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23015-il100,000933.7 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23015-il100,000539.1 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23015-il200,000948.4 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23015-il200,000552.6 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23015-il500,000972 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23015-il500,000574.8 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23015-il1,000,000991 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23015-il1,000,000591.3 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
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