a small aircraft has a wing area of 40 m2 , a lift coefficient of 0.45 at takeoff settings, and a total mass of 4000 kg. determine (a) the takeoff speed of this aircraft at sea level at standard atmospheric conditions, (b) the wing loading, and (c) the required power to maintain a constant cruising speed of 360 km/h for a cruising drag coefficient of 0.035. take the density of air as 1.225 kg/m3 .