Problem-5: In a CD nozzle with a throat area of 0.75 m² of a rocket engine, gas at 7.5 MPa and temperature of 3200 K is in combustion chamber, is expanded fully to (nozzle exit pressure) 10.5 kPa for producing thrust. Assuming flow to be frozen and isentropic, Also, Assume, gamma, y = 1.2 and molecular weight, MW = 24 kg/kmol, Assume, universal gas constant = 8314 J/Kg K mol Determine: (1) the exit Mach number, (2) the maximum exit mass flow rate passing through this nozzle, and (3) the exit area (4) If ambient pressure, i.e. pressure outside nozzle = 10.5 kPa, What is the thrust developed?

Problem-5: In a CD nozzle with a throat area of 0.75 m² of a rocket engine, gas at 7.5 MPa and temperature of 3200 K is in combustion chamber, is expanded fully to (nozzle exit pressure) 10.5 kPa for producing thrust. Assuming flow to be frozen and isentropic, Also, Assume, gamma, y = 1.2 and molecular weight, MW = 24 kg/kmol, Assume, universal gas constant = 8314 J/Kg K mol Determine: (1) the exit Mach number, (2) the maximum exit mass flow rate passing through this nozzle, and (3) the exit area (4) If ambient pressure, i.e. pressure outside nozzle = 10.5 kPa, What is the thrust developed?

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Problem-5: In a CD nozzle with a throat area of 0.75 m² of a rocket engine, gas at 7.5 MPa and temperature of 3200 K is in
combustion chamber, is expanded fully to (nozzle exit pressure) 10.5 kPa for producing thrust. Assuming flow to be
frozen and isentropic, Also, Assume, gamma, y 1.2 and molecular weight, MW = 24 kg/kmol, Assume, universal gas
=
constant = 8314 J/Kg K mol
Determine:
(1) the exit Mach number,
(2) the maximum exit mass flow rate passing through this nozzle, and
(3) the exit area
(4) If ambient pressure, i.e. pressure outside nozzle = 10.5 kPa, What is the thrust developed?
Fuel
Oxidant
Combustion
zone
Mixture of
Hot gas at
high pressure
and Temprature
Expansion
Through Nozzle
High
velocity
exhaust
Liquid
Propellant
Rocket

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