NACA Chord Balance point

Does anybody know how to mathmatically tell where the balance point
should be on a NACA 63-015 airfoil? On a single number NACA airfoil,
like NACA 0012, the number represents the balance point in percent
from the big end. With two number airfoils, how do you figure it out?
Is it 15% from the big end, 63% from the small end, or something else
all together? Does anybody know?

Dennis H.



Dennis Hawkins
n4mwd AT amsat DOT org (humans know what to do)

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