A 60,000 kg airplane is cruising with an angle of attack of 8o and a velocity of 140 m/s at a high altitude where air density is 0. 8 kg/m3. It is operated with no-flap wings having a planform area of 130 m2. (12 marks) (a) Determine lift force (in kN), drag force (in kN), and the power required to overcome drag (in kW) (b) To achieve maximum lift and avoid engine stall, what is the maximum angle of attack that can be increased to (in degree)? What are the minimum velocity (in m/s)? What is the safe minimum velocity (based on the Federal Aviation Administration) (in m/s)?.