The comubstion chamber of a liquid-H_2/liquid-O_2 fueled rocket produces a steady-state-steady-flow of H2O(superheated steam) into the nozzle at (1) at 80 bar and 600C with ke~20 kJ/kg. THe steam exits the nozzle (2) at supersonic speed (1500m/s) at .70 bar as a mixture with x_2=.9. There is no work but heat transfer from the hot combustion chamber and nozzle are large. Neglect changes in potential energy. Given liquid flows: m_H_2, in = 100 kg/s, m_O_2, in= 800 kg/s. T_surr = 300K
Find the entropy production rate for the nozzle. The exit velocity for a reversible and adiabatic nozzle and find the nozzle isentropic efficiency.