Question: (a) Consider compressible flow in a converging-diverging nozzle system. Define the Mach number and outline typical range values for different types of flow. [ 5

 (a) Consider compressible flow in a converging-diverging nozzle system. Define the

(a) Consider compressible flow in a converging-diverging nozzle system. Define the Mach number and outline typical range values for different types of flow. [ 5 marks] (b) Describe how pressure and velocity vary with the Mach number, in the direction of flow, in (i) a subsonic diffuser, (ii) a subsonic nozzle; (iii) a supersonic diffuser and (iv) a supersonic nozzle. [8 marks] (c) Air flows isentropically in a converging-diverging nozzle with a throat area A, where A=3cm2. At some point downstream the inlet, at section A1, the pressure is given by P1=101kPa; the temperature is T1=300K and the flow velocity is V1=868m/s. Determine: (i) If the nozzle is choked. [ 2 marks] (ii) The cross-sectional area A1. [2 marks] (iii) The stagnation pressure Po and temperature T0. [ 3 marks] (iv) The mass flow rate through the nozzle. [3 marks] (v) The critical density at the throat. [2 marks] [Total 25 marks]

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