In this question you will consider the performance of a modified jet-propulsion cycle, for a turbojet engine with a normal-shock inlet, such as equipped on the Commonwealth Aircraft Corporation F86 Sabre (Figure Q1). Figure Q1 Consider an aircraft flying at the conditions specified in Table Q1.A. Table Q1.A: Flight Conditions: P 50kPa Too 203K The engine operates on a cycle that may be modelled as an idealized jet-propulsion cycle, with the following modifications and assumptions: Tp 8 Mo 1.4 The diffuser has a normal shock followed by an isentropic deceleration. The turbine operates with an isentropic efficiency of 90%. The exhaust leaves the nozzle in an ideally expanded state. A summary of key cycle parameters is provided in Table Q1.B. Note that heat input into the combustor is provided in terms of a change in specific entropy AS combustor: Table Q1.B Engine Cycle Specifications: ncomp 1.0 turb 0.9 A) Calculate the temperature and pressure at each state in the cycle B) Calculate the propulsive efficiency of the engine. C) Calculate the exit-to-throat area ratio and exit Mach number. As combustor 1000J/kg.K Assume cp = 1005J/kg.K, c = 718]/kg.K