An airfoil has a mean camber line that has the shape of a circular arc (constant tadius of curvature). The maximum mean camber is ke, where k is a constant and c is the chord. The free-stream velocity is Vo, and the angle of attack is a. Under the assumptiorn that k 《 1, γ distribution is approximately 1 + cos θ 1) Find the angle of zero lift (OL=0) 2) Find the moment coefficient about the leading edge. Cm. te 2) Find the moment coefficient about the aerodynamic center. Cm, ac) (i f n = 1) (ifn关1) 0 0