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NACA 23018 (naca23018-il)

NACA 23018 - NACA 23018 airfoil


Airfoil naca23018-il
Details Dat file Parser  
(naca23018-il) NACA 23018
NACA 23018 airfoil
Max thickness 18% 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 23018
1.0000     0.0019
0.9500     0.0132
0.9000     0.0239
0.8000     0.0440
0.7000     0.0618
0.6000     0.0775
0.5000     0.0905
0.4000     0.1004
0.3000     0.1055
0.2500     0.1056
0.2000     0.1036
0.1500     0.0986
0.1000     0.0883
0.0750     0.0801
0.0500     0.0692
0.0250     0.0529
0.0125     0.0409
0.0000     0.0000
0.0125     -0.0183
0.0250     -0.0271
0.0500     -0.0380
0.0750     -0.0460
0.1000     -0.0522
0.1500     -0.0618
0.2000     -0.0686
0.2500     -0.0727
0.3000     -0.0747
0.4000     -0.0737
0.5000     -0.0681
0.6000     -0.0594
0.7000     -0.0482
0.8000     -0.0348
0.9000     -0.0194
0.9500     -0.0109
1.0000     -0.0019
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Lednicer format dat file
Selig format dat file

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Polars for NACA 23018 (naca23018-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca23018-il50,000921.1 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23018-il50,000526.2 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23018-il100,000936.1 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23018-il100,000538.2 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23018-il200,000950 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23018-il200,000550.8 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23018-il500,000971.3 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23018-il500,000570 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23018-il1,000,000989.9 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23018-il1,000,000584.6 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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