The nozzle in Problem 16.50 will have a throat area of 0.001272 m and an exit area 2.896 times as large. Suppose the back pressure is raised to 1.4 MPa and that the flow remains isentropic except for a normal shock wave. Verify that the shock mach number (Mx) is close to 2 and find the exit mach number, the temperature and the mass flow rate through the nozzle.