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NACA 2421 (naca2421-il)

NACA 2421 - NACA 2421 airfoil


Airfoil naca2421-il
Details Dat file Parser  
(naca2421-il) NACA 2421
NACA 2421 airfoil
Max thickness 21% 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 2421
1.0000     0.0022
0.9500     0.0176
0.9000     0.0318
0.8000     0.0574
0.7000     0.0794
0.6000     0.0979
0.5000     0.1122
0.4000     0.1216
0.3000     0.1238
0.2500     0.1215
0.2000     0.1159
0.1500     0.1070
0.1000     0.0928
0.0750     0.0829
0.0500     0.0700
0.0250     0.0521
0.0125     0.0387
0.0000     0.0000
0.0125     -0.0282
0.0250     -0.0402
0.0500     -0.0551
0.0750     -0.0648
0.1000     -0.0718
0.1500     -0.0805
0.2000     -0.0852
0.2500     -0.0867
0.3000     -0.0862
0.4000     -0.0816
0.5000     -0.0731
0.6000     -0.0617
0.7000     -0.0487
0.8000     -0.0344
0.9000     -0.0188
0.9500     -0.0106
1.0000     -0.0022
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Lednicer format dat file
Selig format dat file

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Polars for NACA 2421 (naca2421-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca2421-il50,00096.9 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2421-il50,000523.8 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2421-il100,000939.5 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2421-il100,000541.1 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2421-il200,000957.5 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2421-il200,000553.3 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2421-il500,000975.5 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2421-il500,000567.6 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2421-il1,000,000989.5 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2421-il1,000,000581.1 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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