Find the throat pressure and temperature for reversible

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1. Air flows into a convergent-divergent nozzle with an exit area 2.0 times the throat area of 0.005 m2. The inlet stagnation state is 1.2 MPa, 600 K. Find the back pressure that will cause a reversible supersonic exit flow with M = 1 at the throat. What is the mass flow rate?

2. What is the exit pressure that will allow a reversible subsonic exit flow in the previous problem?

3. Helium flows at 500 kPa, 500 K, with 100 m/s into a convergent-divergent nozzle. Find the throat pressure and temperature for reversible flow and M = 1 at the throat.

Reference no: EM131238503

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