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NACA 0018 (naca0018-il)

NACA 0018 - NACA 0018 airfoil


Airfoil naca0018-il
Details Dat file Parser  
(naca0018-il) NACA 0018
NACA 0018 airfoil
Max thickness 18% 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 0018
1.0000     0.00189
0.9500     0.01210
0.9000     0.02172
0.8000     0.03935
0.7000     0.05496
0.6000     0.06845
0.5000     0.07941
0.4000     0.08705
0.3000     0.09003
0.2500     0.08912
0.2000     0.08606
0.1500     0.08018
0.1000     0.07024
0.0750     0.06300
0.0500     0.05332
0.0250     0.03922
0.0125     0.02841
0.0000     0.00000
0.0125     -0.02841
0.0250     -0.03922
0.0500     -0.05332
0.0750     -0.06300
0.1000     -0.07024
0.1500     -0.08018
0.2000     -0.08606
0.2500     -0.08912
0.3000     -0.09003
0.4000     -0.08705
0.5000     -0.07941
0.6000     -0.06845
0.7000     -0.05496
0.8000     -0.03935
0.9000     -0.02172
0.9500     -0.01210
1.0000     -0.00189
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Lednicer format dat file
Selig format dat file

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Polars for NACA 0018 (naca0018-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca0018-il50,000922.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0018-il50,000526.4 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0018-il100,000937.5 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0018-il100,000538.1 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0018-il200,000950.1 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0018-il200,000548 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0018-il500,000965.8 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0018-il500,000561.5 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0018-il1,000,000977.9 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0018-il1,000,000573.7 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
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