metal249
New Member
Hello all, new member here from Tucson. I'm in the drafting phase of building a part 103 UL from scratch and I've come to a snag. I've been learning the science behind airfoil shapes and have picked my airfoil(naca 4418). I did all the math from Chris Heintz's article (http://www.zenithair.com/kit-data/ch-design-made-simple-p1.pdf) and have come up with approximate performance numbers for my theoretical ultralight. I have come up with these numbers;
Mean aerodynamic chord= 6ft
Area= 168 sq. ft.
Span= 28 ft.
What I don't understand, is how to physically construct the naca 4418 shape for the wing segments. Any insight would be greatly appreciated.
Mean aerodynamic chord= 6ft
Area= 168 sq. ft.
Span= 28 ft.
What I don't understand, is how to physically construct the naca 4418 shape for the wing segments. Any insight would be greatly appreciated.
