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