A plane is flying at an altitude of 10,000 meters and a speed of \(810 \mathrm{~km} / \mathrm{hr}\). The fuselage of the plane can be considered a cylinder of diameter \(4 \mathrm{~m}\) and length \(20 \mathrm{~m}\) and the wing area is \(110 \mathrm{~m}^{2}\) (2 rectangular plates each of dimensions \(11 \mathrm{~m} \times 5 \mathrm{~m}\) ). The aircraft weighs

\(40,000 \mathrm{~kg}\). You may assume the air density at that altitude is \(0.45 \mathrm{~kg} / \mathrm{m}^{3}\). What is the lift coefficient required for this plane? If the angle of attack required is 18 times the lift coefficient, what angle of attack is required? Calculate the drag force on the plane considering both the fuselage and wing components.