GATE_AE_2027_MOCK_02_Q57
GATE 2027 Aerospace Engineering All-India Master Mock 02 (Compressible Aerodynamics & High-Speed Propulsion)
MCQ · 2 Marks
Propulsion • Inlets, Combustors & Nozzles • Combustion Chambers & Total Pressure Loss
In a gas turbine combustor, Rayleigh flow analysis indicates that adding heat at subsonic Mach numbers results in:
(A) Decrease in stagnation pressure and increase in Mach number
(B) Increase in stagnation pressure and decrease in Mach number
(C) Constant stagnation pressure with supersonic acceleration
(D) Decrease in static temperature only
Answer Key:
A
Step-by-Step Verified Solution
### Solution: Heat addition to a subsonic flow accelerates the flow ($M$ increases toward 1) and causes an unavoidable loss of stagnation pressure ($p_{02} < p_{01}$) due to thermal throttling. Correct: A.