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NACA 0024 (naca0024-il)

NACA 0024 - NACA 0024 airfoil


Airfoil naca0024-il
Details Dat file Parser  
(naca0024-il) NACA 0024
NACA 0024 airfoil
Max thickness 24% 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 0024
1.0000     0.00252
0.9500     0.01613
0.9000     0.02896
0.8000     0.05247
0.7000     0.07328
0.6000     0.09127
0.5000     0.10588
0.4000     0.11607
0.3000     0.12004
0.2500     0.11883
0.2000     0.11475
0.1500     0.10691
0.1000     0.09365
0.0750     0.08400
0.0500     0.07109
0.0250     0.05229
0.0125     0.03788
0.0000     0.00000
0.0125     -0.03788
0.0250     -0.05229
0.0500     -0.07109
0.0750     -0.08400
0.1000     -0.09365
0.1500     -0.10691
0.2000     -0.11475
0.2500     -0.11883
0.3000     -0.12004
0.4000     -0.11607
0.5000     -0.10588
0.6000     -0.09127
0.7000     -0.07328
0.8000     -0.05247
0.9000     -0.02896
0.9500     -0.01613
1.0000     -0.00252
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Lednicer format dat file
Selig format dat file

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Polars for NACA 0024 (naca0024-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca0024-il50,000915.4 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0024-il50,000521.6 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0024-il100,000934.7 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0024-il100,000530.6 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0024-il200,000943 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0024-il200,000537 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0024-il500,000952.1 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0024-il500,000550.8 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca0024-il1,000,000968.8 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   naca0024-il1,000,000564.1 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
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