Arocket vehicle is used to carry a payload of sulfur dioxide into the atmosphere along a vertical flight path. the rocket engine consists of a combustion chamber connected to a convergent-divergent nozzle having exit/throat area ratio of 3: 1. it is powered by propellants of hydrogen and oxygen, which react fully to form water vapour (molar mass 18 kg/kmol), giving a temperature and pressure of 2900 k and 20 bar respectively in the combustion chamber. the propellants have total initial mass of 500 kg. a) with the of the gas dynamics chart provided in the appendix, calculate the specific impulse of the rocket engine at lift off. b) thus, calculate the total mass flow of propellant to achieve a thrust of 30 kn and calculate the nozzle throat area accordingly. c) assuming that the mass flow and thrust remain constant during flight, and that the rocket has an effective mean mass of 2000 kg, estimate the height reached by the rocket, and the vertical velocity achieved, at the moment when the fuel runs out. d) the rocket continues to coast upwards without fuel. calculate its final altitude, assuming that the total mass is now reduced to 1750 kg. you should take into account air resistance. the frontal area of the rocket vehicle is 0.9 m^2, the drag coefficient is 0.55, and the air density is approximately 0.6 kg/m^3 throughout flight.