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NACA 2410 (naca2410-il)

NACA 2410 - NACA 2410 airfoil


Airfoil naca2410-il
Details Dat file Parser  
(naca2410-il) NACA 2410
NACA 2410 airfoil
Max thickness 10% at 29.9% chord.
Max camber 2% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 2410
1.00000     0.00105
0.95041     0.00990
0.90067     0.01816
0.80097     0.03296
0.70102     0.04551
0.60085     0.05580
0.50049     0.06356
0.40000     0.06837
0.29875     0.06875
0.24814     0.06668
0.19761     0.06276
0.14722     0.05665
0.09710     0.04766
0.07217     0.04169
0.04742     0.03420
0.02297     0.02411
0.01098     0.01694
0.00000     0.00000
0.01402     -0.01448
0.02703     -0.01927
0.05258     -0.02482
0.07783     -0.02809
0.10290     -0.03016
0.15278     -0.03227
0.20239     -0.03276
0.25186     -0.03230
0.30125     -0.03125
0.40000     -0.02837
0.49951     -0.02468
0.59915     -0.02024
0.69898     -0.01551
0.79903     -0.01074
0.89933     -0.00594
0.94959     -0.00352
1.00000     -0.00105
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Selig format dat file

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Polars for NACA 2410 (naca2410-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca2410-il50,000935.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2410-il50,000536.1 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2410-il100,000951.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2410-il100,000549.9 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2410-il200,000967.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2410-il200,000562 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2410-il500,000986.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2410-il500,000575.4 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2410-il1,000,000998.5 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2410-il1,000,000583.7 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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