An airflow at 25-degrees C and 50 kPa with a velocity of 900 m/s is turned by an abrupt 25-degree corner with a weak oblique shock. Estimate the pressure (in kPa), velocity (in m/s), and Mach number after the corner. 110 kPa, 540 m/s, 1.38 124 kPa, 602 m/s, 1.51 144 kPa. 668 m/s, 1.72 162 kPa, 689 m/s. 1.80 None of the above

Consider a system where a horizontal, laminar, separated flow of air and water at 100 kPa pressure and 20 C temperature are moving between two infinitely-sized parallel plates. The water flow is not forced, but is carried along by the air flow. The 'superficial velocity' of the air is 0.1 m/s (superficial velocity is volume flow rate / flow area, representing the average velocity of the flow). The depth of the water film is 2 mm and the thickness of the air layer is 5 mm. Use the multiphase balance equations and interfacial boundary conditions to derive the velocity profile in the air and water, with y=D0 being the interface between the two.