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NACA 2418 (naca2418-il)

NACA 2418 - NACA 2418 airfoil


Airfoil naca2418-il
Details Dat file Parser  
(naca2418-il) NACA 2418
NACA 2418 airfoil
Max thickness 18% at 30% chord.
Max camber 2% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 2418
1.0000     0.0019
0.9500     0.0155
0.9000     0.0281
0.8000     0.0508
0.7000     0.0702
0.6000     0.0865
0.5000     0.0989
0.4000     0.1071
0.3000     0.1088
0.2500     0.1065
0.2000     0.1015
0.1500     0.0934
0.1000     0.0805
0.0750     0.0717
0.0500     0.0603
0.0250     0.0445
0.0125     0.0328
0.0000     0.0000
0.0125     -0.0245
0.0250     -0.0344
0.0500     -0.0468
0.0750     -0.0548
0.1000     -0.0603
0.1500     -0.0674
0.2000     -0.0709
0.2500     -0.0718
0.3000     -0.0712
0.4000     -0.0671
0.5000     -0.0599
0.6000     -0.0504
0.7000     -0.0397
0.8000     -0.0280
0.9000     -0.0153
0.9500     -0.0087
1.0000     -0.0019
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Lednicer format dat file
Selig format dat file

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Polars for NACA 2418 (naca2418-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca2418-il50,00098.6 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2418-il50,000527.3 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2418-il100,000942.9 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2418-il100,000544 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2418-il200,000960.8 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2418-il200,000558.6 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2418-il500,000983.4 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2418-il500,000575.3 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2418-il1,000,000997.1 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2418-il1,000,000587.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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