Air enters a constant area combustor followed by a convergent nozzle. Heat addition takes place in the combustor and the flow is isentropic in the nozzle. The inlet Mach number is 0.3, and the throat-to-inlet area ratio is 0.9.

(a) If the stagnation temperature is doubled in the combustor, determine the exit Mach number.

(b) Determine the stagnation temperature rise that will just cause the nozzle to choke.

(c) If the actual rise in stagnation temperature is 10% higher than the value obtained in (b), determine the inlet Mach number.

(d) If the mass flow rate is the same, determine the required change in the inlet stagnation pressure.