Aerospace Engineering > GATE 2010 > Nozzle Flow
The stagnation pressure and stagnation temperature inside the combustion chamber of a liquid
rocket engine are 1.5 MPa and 2500 K respectively. The burned gases have γ=1.2 and
R=692.83 J/kgK. The rocket has a converging - diverging nozzle with a throat area of 0.025 m2
and the flow at the exit of the nozzle is supersonic. If the flow through the nozzle is isentropic, what
is the mass flow rate of the gases out of the nozzle?
rocket engine are 1.5 MPa and 2500 K respectively. The burned gases have γ=1.2 and
R=692.83 J/kgK. The rocket has a converging - diverging nozzle with a throat area of 0.025 m2
and the flow at the exit of the nozzle is supersonic. If the flow through the nozzle is isentropic, what
is the mass flow rate of the gases out of the nozzle?
Correct : c
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