An airplane has a rectangular-platform wing that has an elleiptical spanwise lift distribution. the airplane has a mass of 1200 kg, a wing area of 20 m^2, and a wingspan of 14 m, and it is flying at 60 m/s at 3000 m altitude in a standard atmosphere. if the form drag coefficient is .01, calculate the total drag on the wing and the power (p=FV) necessary to overcome the drag.