- Consider The Continuous Flow Fixed Geometry Supersonic Wind Tunnel Of The Figure Where Flow Is Clockwise Around The S 1 (106.99 KiB) Viewed 14 times
- Consider The Continuous Flow Fixed Geometry Supersonic Wind Tunnel Of The Figure Where Flow Is Clockwise Around The S 2 (122.04 KiB) Viewed 14 times
- Consider The Continuous Flow Fixed Geometry Supersonic Wind Tunnel Of The Figure Where Flow Is Clockwise Around The S 3 (166.88 KiB) Viewed 14 times
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
Nozzle Test section Diffuser Compressor Cooler who tw
a) (Anh) The throat area of the nozzle. (3 points) b) (Ath) 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) c) (Mth) 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)