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NACA 64A410 (naca64a410-il)

NACA 64A410 - NACA 64A410 airfoil


Airfoil naca64a410-il
Details Dat file Parser  
(naca64a410-il) NACA 64A410
NACA 64A410 airfoil
Max thickness 10% at 39.9% chord.
Max camber 2.7% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 64A410
1.00000     0.00021
0.95053     0.01028
0.90104     0.02038
0.85148     0.03018
0.80151     0.03967
0.75126     0.04780
0.70108     0.05480
0.65085     0.06106
0.60057     0.06624
0.55025     0.07040
0.49989     0.07344
0.44950     0.07522
0.39910     0.07552
0.34871     0.07414
0.29834     0.07131
0.24800     0.06705
0.19770     0.06126
0.14748     0.05366
0.09737     0.04380
0.07230     0.03865
0.04749     0.03034
0.02276     0.02095
0.01059     0.01451
0.00582     0.01112
0.00350     0.00902
0.00000     0.00000
0.00650     -0.00678
0.00918     -0.00796
0.01441     -0.00969
0.02724     -0.01251
0.05251     -0.01592
0.07770     -0.01919
0.10263     -0.01996
0.15252     -0.02244
0.20230     -0.02406
0.25200     -0.02499
0.30166     -0.02537
0.35129     -0.02518
0.40090     -0.02436
0.45050     -0.02266
0.50011     -0.02024
0.54975     -0.01736
0.59943     -0.01418
0.64915     -0.01086
0.69892     -0.00760
0.74874     -0.00460
0.79849     -0.00229
0.84852     -0.00132
0.89896     -0.00076
0.94947     -0.00048
1.00000     -0.00021
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Lednicer format dat file
Selig format dat file

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Polars for NACA 64A410 (naca64a410-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca64a410-il50,000938.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca64a410-il50,000537.5 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca64a410-il100,000958.2 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca64a410-il100,000555.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca64a410-il200,000979 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca64a410-il200,000571.3 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca64a410-il500,0009100.7 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca64a410-il500,000575.2 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca64a410-il1,000,000998.6 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca64a410-il1,000,000580.9 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
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