Question: In a hydrogen-powered rocket, hydrogen enters a nozzle at a very low velocity with a temperature and pressure of 2000°C and 6.8 MPa, respectively. The pressure on the exit plane of the nozzle is equal to the ambient pressure, which is 10 kPa. If the required thrust is 10 MN, what hydrogen mass flow rate is required? The flow through the nozzle can be assumed to be isentropic and the specific heat ratio of the hydrogen can be assumed to be 1.4.