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NACA 16-018 (naca16018-il)

NACA 16-018 - NACA 16-018 airfoil


Airfoil naca16018-il
Details Dat file Parser  
(naca16018-il) NACA 16-018
NACA 16-018 airfoil
Max thickness 18% 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 16-018
1.0000     0.00180
0.9500     0.02122
0.9000     0.03776
0.8000     0.06298
0.7000     0.07904
0.6000     0.08752
0.5000     0.09000
0.4000     0.08782
0.3000     0.08126
0.2000     0.06996
0.1500     0.06202
0.1000     0.05186
0.0750     0.04548
0.0500     0.03764
0.0250     0.02708
0.0125     0.01938
0.0000     0.00000
0.0125     -0.01938
0.0250     -0.02708
0.0500     -0.03764
0.0750     -0.04548
0.1000     -0.05186
0.1500     -0.06202
0.2000     -0.06996
0.3000     -0.08126
0.4000     -0.08782
0.5000     -0.09000
0.6000     -0.08752
0.7000     -0.07904
0.8000     -0.06298
0.9000     -0.03776
0.9500     -0.02122
1.0000     -0.00180
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Selig format dat file

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Polars for NACA 16-018 (naca16018-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca16018-il50,000922.6 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16018-il50,000520.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16018-il100,000928.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16018-il100,000524.4 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16018-il200,000937.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16018-il200,000530 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16018-il500,000944.5 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16018-il500,000533.3 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca16018-il1,000,000947.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca16018-il1,000,000540.5 at α=11°Mach=0 Ncrit=5Xfoil predictionDetails
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