Has anyone tried computing the section modulus of the front center spar?
I should probably wait until tomorrow to check my work but I get I=36.7 in4 (152.7cm4). Z = I/c so Z= 10.2in3 (41.5cm3). I used dimensions from my CAD drawings and they are before any trimming for the airfoil but I think the difference is insignificant. Are these numbers close to what you got? Do I need to go back and do it over? Pete
