Consider a turbojet engine (no-afterburner) cruising at M=0.85, at 40,000 ft (Pa = 18.75kPa and Ta=217K), with fixed m

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answerhappygod
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Consider a turbojet engine (no-afterburner) cruising at M=0.85, at 40,000 ft (Pa = 18.75kPa and Ta=217K), with fixed m

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Consider a turbojet engine (no-afterburner) cruising at M=0.85, at 40,000 ft (Pa =

18.75kPa and Ta=217K), with fixed maximum temperature T04=1600K. Why does the

specific thrust emerge as a non-monotonic function (increases and then decreases) of

the compressor pressure ratio? Explain with analysis and brief thermodynamic

arguments. Assume relevant adiabatic efficiencies, if required.
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