Consider the NACA 4412 airfoil data on page 586 (Introduction to Aircraft Flight Mechanics, T. R. Yechout, 2003). Airfoil chord c is 4 ft and flight altitude H is 15,000 ft. Assume a simple flight model of L = W and T = D where weight W = 100 lbf/ft, thrust T = Tmax8Th, Tmax = 10 lbf/ft, and dimensionless throttle 8Th has the range 0 8Th 1. a) For flap deflection 8F = 0, Reynolds number R = 6106, and standard roughness, compute o, Clo, Cla, Cdo = Cdmin, cdo, k, Cmac' b) For attack angle = 0 and Reynolds number R = 6106, compute CISF C18F CmacF c) Suppose the aircraft is flying with SF = 5 deg and 8Th = 0.2. Compute the steady state values. for velocity V and attack angle a. d) Plot xcp vs. for SF = 0 over the range -16 +16 deg.