[10 pts] Consider an aircraft gliding downward with constant velocity. The aircraft travels with constant velocity U., lift coefficient CL, and glide angle 0. The aircraft has weight W, wing area S, and travels through air of density p. Use C = 0.5, U∞ = 60 m/s, W = 45 kN, S = 40 m², and p = 1.23 kg/m³. a. Calculate the aircraft's glide angle b. Calculate the aircraft's drag coefficient Hint: Begin the analysis by drawing a free body diagram of the aircraft. U_ Θ