Superheated steam from a large reservoir in which the pressure is 1 MPa flows adiabatically through a convergent-divergent nozzle for which the cross-sectional area at exit is twice that at the throat. The pressure beyond the exit is 700 kPa. Determine the Mach number of the flow in the exit plane, the crosssectional area at the plane where a normal shock may be expected in the nozzle, and the Mach number immediately upstream of the shock. What ambient pressure at exit would be necessary to produce isentropic supersonic flow without shocks? What exit pressure would give the same mass flow rate but with subsonic conditions throughout? Assume that frictional effects are negligible, that γ for superheated steam = 1.3, and that the steam remains superheated and with constant specific heat capacities throughout.