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EAS201: A turbojet engine with combustor exit temperature of 1573 K is to be designed for optimum: Aerospace Propulsion Assignment, SUSS

Question 3
A turbojet engine with combustor exit temperature of 1573 K is to be designed for optimum operations in 233 K ambient temperature. Assume ideal conditions without losses. Take low the heating value of jet fuel as 42,800 kJ/kg, and cp and γ for air as 1.004 kJ/(kg.K) and 1.4, respectively.

Question 3a
Compute the compressor pressure ratio such that the engine provides maximum specific thrust when operating at Mach 2.0 with afterburner.
Question 3b
With the compressor pressure ratio that you have determined in Question 3a, the engine is also to cruise in the same ambient conditions but at a subsonic speed. Analyse the performance of the engine when operating without afterburner.
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Question 3b(i)
Predict the optimum subsonic Mach number such that the engine specific thrust is maximum.

Question 3b(ii)
Determine the maximum specific thrust.

Question 3a(ii)
Solve the subsonic cruise thrust specific fuel consumption.
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