Consider an airplane cruising at an altitude of 30 km where standard atmospheric conditions are (- 50°c) and 26.5 kpa at a speed of 800 km/h. each wing of the airplane can be modeled as a 25m x 3m flat plate, and the friction coefficient of the wings is 0.0016 and its surface temperature is 10°c: a) draw the schematic of the system. b) using the c-c analogy, determine the heat transfer coefficient and the rate of heat transfer for the wings at cruising conditions.