A Mach 2 wind tunnel was designed in the standard configuration: a large tank containing air of pressure 200 kPa, temperature 100 C, Cp = 1000 J/kgK, R = 287 J/kgK, and gamma =1.4, a converging-diverging nozzle, and an exit flow that exhausts into an open testing room.

The wind tunnel can support 60 kPa pressure differently.

The wind tunnel exploded during the operation, and before it explode the measured exit speed is 160 m/s.

Please DONT COPY OTHERS, and show all the detailed calculations.

1. Determine if the flow is isotropic in the wind tunnel.

2. Determine the flow is choked or not at the throat.

3. Determine which part in the wind tunnel will explode?

Po=2ookla Vext=160 m/s To=100C