Here we cover a Thermodynamic Problem: Pressures and Temperatures of aircraft engines, which you may face during your university studies. It is centred around an aircraft engine intake and the relevant temperatures and pressures associated. It is a great application of thermodynamics and gives a great visualisation of thermodynamics in the real world.

You will need a compliant calculator for your university studies. I have listed some here in the event you need one. Also, the equations I have used are found in the Engineering Data Book found on this page. It was a great tool for me to use during my university studies. Although, you are provided one in an exam, I would recommend having your own copy.

Problem

i) A Mach 1.5 aircraft flies in ambient air where the static pressure = 0.27 bar, the static temperature = 225 K, and the specific heat ratio  = 1.4. What is the maximum stagnation pressure and the stagnation temperature that can be achieved through a shock-free engine intake?

ii) The engine thrust is set so that a normal shock occurs before the intake. What is the stagnation pressure and the stagnation temperature downstream of the shock?

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