Consider an aircraft with two airfoils (wings) with total area A and a total mass of m. Assume (unrealistically), for a case of maximum lift, the air has zero velocity at the bottom of the wing. a. What must the difference of speed of the air going above the airfoils be to support straight and level flight (i.e. lift = weight)? b. If the aircraft is a Boing 747-8 with wing area 554 m and cruising mass of 400,000 kg, what must the air speed be to support straight and level flight? c. Could this aircraft take off with a speed of 200 mph? Why or why not