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NACA 23024 (naca23024-il)

NACA 23024 - NACA 23024 airfoil


Airfoil naca23024-il
Details Dat file Parser  
(naca23024-il) NACA 23024
NACA 23024 airfoil
Max thickness 24% at 30.3% chord.
Max camber 2.9% at 1.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 23024
1.00000     0
0.95036     0.01724
0.90064     0.03115
0.80116     0.05687
0.70162     0.07988
0.60202     0.10008
0.50235     0.11690
0.40256     0.12928
0.30265     0.13546
0.25262     0.13535
0.20253     0.13237
0.15001     0.12528
0.09423     0.11049
0.06601     0.09844
0.03853     0.08172
0.01331     0.05764
0.00277     0.04017
0.00000     0.00000
0.02223     -0.03303
0.03669     -0.04432
0.06147     -0.05862
0.08399     -0.06860
0.10577     -0.07647
0.14999     -0.08852
0.19747     -0.09703
0.24738     -0.10223
0.29735     -0.10454
0.39744     -0.10278
0.49766     -0.09482
0.59798     -0.08242
0.69838     -0.06664
0.79884     -0.04803
0.89936     -0.02673
0.94964     -0.01504
1.00000     0.00000
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Selig format dat file

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Polars for NACA 23024 (naca23024-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca23024-il50,000916.3 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23024-il50,000519.9 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23024-il100,000934.2 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23024-il100,000528.5 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23024-il200,000941.3 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23024-il200,000533.2 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23024-il500,000944.5 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23024-il500,000543.4 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca23024-il1,000,000956.9 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca23024-il1,000,000554.4 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
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