Aerospace Engineering > GATE 2010 > Engine Thermodynamics
An aircraft with an IDEAL Turbojet engine is flying at 200 m/s at an altitude where the ambient pressure is equal to 0.8 bar.
The stagnation pressure and temperature at the inlet of the turbine are 6 bar and 1400 K respectively.
The change in specific enthalpy across the compressor is 335 kJ/kg.
Assume the fuel flow rate to be very small in comparison to the air flow rate and consider
Cp = 1117 J/kg·K and γ = 1.3.
What is the stagnation pressure at the inlet of the nozzle?
What is the stagnation pressure at the inlet of the nozzle?
Correct : b
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