Problem 1 (40%). Applying thin airfoil theory, determine the Fourier coefficients, c, and Cmc for the following cases (include a as an unknown variable in your expression(s)): 4 a) A flat plate with zero camber, y(x) = 0. b) An airfoil with a parabolic camberline, y(x) camber at the semi-chord location (x expression in terms of h. = 4hx(1-x), where h is the maximum 0.5), assuming a unit chord. Leave your =