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NACA 16-021 (naca16021-il)

NACA 16-021 - NACA 16-021 airfoil


Airfoil naca16021-il
Details Dat file Parser  
(naca16021-il) NACA 16-021
NACA 16-021 airfoil
Max thickness 21% 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 16-021
1.0000     0.00210
0.9500     0.02476
0.9000     0.04405
0.8000     0.07348
0.7000     0.09221
0.6000     0.10211
0.5000     0.10500
0.4000     0.10246
0.3000     0.09480
0.2000     0.08162
0.1500     0.07236
0.1000     0.06050
0.0750     0.05306
0.0500     0.04391
0.0250     0.03159
0.0125     0.02261
0.0000     0.00000
0.0125     -0.02261
0.0250     -0.03159
0.0500     -0.04391
0.0750     -0.05306
0.1000     -0.06050
0.1500     -0.07236
0.2000     -0.08162
0.3000     -0.09480
0.4000     -0.10246
0.5000     -0.10500
0.6000     -0.10211
0.7000     -0.09221
0.8000     -0.07348
0.9000     -0.04405
0.9500     -0.02476
1.0000     -0.00210
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Selig format dat file

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Polars for NACA 16-021 (naca16021-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca16021-il50,000921.9 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16021-il50,000517.9 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16021-il100,000928.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16021-il100,000520.7 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16021-il200,000933.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16021-il200,000526.3 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16021-il500,000939.5 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16021-il500,000528.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16021-il1,000,000942 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16021-il1,000,000531.6 at α=12.75°Mach=0 Ncrit=5Xfoil predictionDetails
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