Consider a flying wing with a wing area of 206 m2 , an aspect ratio of 10, and a span effective factor of 0.9, and an NACA 4412 aerofoil. The weight of the aeroplane is 7.5 x 105 N. If the aeroplane is flying at an altitude of 3 km and the flight velocity is 100 m/s, calculate the total drag on the aircraft. Assume the profile drag coefficient to be approximately 0.006