In: Mechanical Engineering
A rocket motor burns LH2 and LOX. The combustion chamber pressure and temperature are 25 atmospheres and 3517 K, respectively. The area of the nozzle throat is 0.1 m^2. The nozzle exit area is designed so that the exit pressure equals the ambient pressure at 30 km altitude. For the combustion gases, assume gamma is 1.22 and the molecular weight is 16. At an altitude of 30 km, where the local atmospheric pressure is 1186 Pa, calculate (a) the specific impulse, (b) the thrust, (c) the area of the exit, and (d) the exit Mach number