A converging-diverging nozzle with an exit-to-sonic area ratio of A/A = 47, exhausts air from a high-pressure reservoir (T, = 270 K) to the back plane, where the pressure is fixed at p, = 1 atm [abs]. The test section area is A = 0.06 m? and the reservoir has a volume of 50 m. a) Assume that the test is located immediately upstream of the exit and that the flow up to the exit is isentropic, what is the minimum stagnation pressure under which the tunnel will start?

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(Q) A converging-diverging nozzle discharges an over-expanded jet into a room. Calculate the deflection angle in degrees caused by the oblique shock forming at the nozzle exit? Ratio between the room pressure and the pressure at the nozzle exit is 5.4. Mach number at the nozzle exit is 1.5. Assume the fluid to be air as a perfect gas with k=1.4

b) In a converging-diverging duct the flow conditions are such that a normal shock is formed at the exit of the diverging section. Upstream of the shock the flow conditions are as below. Mach number= '5.198', Pressure= '311886.9' Pa and Temperature= '228.72' K. Obtain the Mach number, pressure, and temperature at the downstream of the shock. Assume standard air properties (y=1.4).