Consider an aircraft with a gross weight of 8 tons cruising at a speed of 360 km/h. It can be assumed that the wing is elliptic with a span of 15 m and an aspect ratio of 8. Calculate: a) Lift coefficient b) Lift force at the center of the wing c) Induced angle of attack d) Induced drag coefficient. The density of air at this cruising altitude is 1 kg/m.