Figure 10.28 illustrates the lift-to-drag ratio, F_{L}/F_{D} = C_{L}/C_{D} versus different angles of attack, α for a typical cambered (nonsymmetrical) airfoil. Consider an airplane that weighs 50,000lb with cambered (nonsymmetrical) wings with a span width of 40 ft and a chord length of 35 ft, as illustrated in Figure EP 10.22. Assume that the airplane cruises at an altitude of 45,000 ft (air at standard atmosphere at an altitude of 45,000 ft, \rho = 0.00046227 slugs/ft^{3} ) at a steady cruising speed of 300 mph. (a) Determine the lift force and the drag force acting on the aircraft wings during steady cruising speed at the target operating point for the airfoil.