The main engine of the Space Shuttle utilizes a converging-diverging nozzle toexpand high-pressure, high-temperature propellant to very high exhaustspeeds. Let's calculate the engine's performance by assuming ideal gas andconstant=1.2 throughout our calculations. Operation is steady state.a) The rocket engine combusts liquid hydrogen, H2with liquid oxygen,O2after they are mixed at an average boiling temperature of Tb= 70K. Theheat released per unit mass during the approximately isobaric combustion is13 MJ/kg. (Also referred to as the heat of combustion similar to the heat ofvaporization we discussed in class.) It raises the stagnation temperature toTo=3000K at stagnation pressure of po=200atm. Use the first law ofthermodynamics to calculate the molecular weight of the combusted propellantmixture and then calculate its density. (We can assume that the combustionchamber is a closed system.)