At what Mach number will the normal shock occur in the nozzle of Problem 15.53 if the back pressure is 1.4 MPa? (Trial and error on Mx)
Problem 15.53
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?