A rocket engine uses liquid hydrazine (N2 H4) as a fuel and pure oxygen at 25 8C as the oxidizer. Hydrazine has an enthalpy of formation of 2 50 410 kJ/kmol. The oxygen is supplied to the engine with an oxygen-fuel ratio of 3. The heat loss from the combustor is 200 kJ/kg of N2 H4 burned. Calculate the flame temperature just before the nozzle assuming a constant-pressure combustion chamber.