Answer Happy

Consider the continuous-flow, fixed-geometry, supersonic wind tunnel of the figure, where flow is clockwise around the system. During steady-state operation the flow conditions in the Test Section are: Test Section Area: A=200 cm Design Mach Number, MDesign = 2.3 Static Temperature: T = 230 K Static Pressure: P = 30 kPa Detemine: a) (Atn) The throat area of the nozzle. (3 points) b) (Ah) The throat area of the diffuser (minimum) which will allow start-up (i.e., allow the shock to be swallowed) at the design Mach number. (3 points) €) (Min) The Mach number at the diffuser throat which will allow the minimum loss of stagnation pressure during steady-state operation at design conditions. (3 points) d) (Poy / Pox )min The minimum stagnation pressure loss across the shock (at the diffuser throat) during steady-state operation at design conditions. (3 points) e) m The mass-flow rate during operating conditions (3 points) Nozzle Test section Diffuser M> 1 Compressor Cooler w