Consider an airplane cruising at an altitude of 10 km where standard atmospheric conditions are –50°c and 26.5 kpa at a speed of 990 km/h. each wing of the airplane can be modeled as a 25-m × 3-m flat plate, and the friction coefficient of the wings is 0.0016. using the momentum-heat transfer analogy, determine the heat transfer coefficient for the wings at cruising conditions. the properties of air at –50°c and 1 atm are: cp =0.999 kj/kg·kpr = 0.7440