Question
In: Mechanical Engineering
A converging-diverging rocket nozzle is connected to a combustion chamber filled with gas at a total...
A converging-diverging rocket nozzle is connected to a combustion chamber filled with gas at a total pressure of 1200 kPa and a total temperature of 2400 K. The design exit Mach number is 2.9 and the nozzle throat area is 50 cm2 . Assume the gas behaves as an ideal gas with k = 1.3 and a molecular weight of 24 kg/kmol. Determine (a) The back pressure necessary to induce the design Mach number at the nozzle exit. (b) The design exit area for isentropic supersonic flow. (c) The static pressure at the throat when the flow is choked. (d) The mass flow rate through the nozzle when the flow is choked.
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samet mamat answered 4 months agoRelated Solutions
Air flows in a converging-diverging nozzle. The nozzle throat area is 50 cm2. The total pressure...
Air flows in a converging-diverging nozzle. The nozzle throat
area is 50 cm2. The total pressure at the nozzle inlet is 1 MPa.
The total pressure at the nozzle exit is 650 kPa. The Mach number
at the nozzle exit is 0.70. Find the nozzle exit area.
51.7 cm2
84.2 cm2
35.6 cm2
54.7 cm2
1. Air enters a converging-diverging nozzle with a total pressure of 1100 kPa and a total temperature...
1. Air enters a
converging-diverging nozzle with a total pressure of 1100 kPa and a
total temperature of 127°C. The exit area to throat area
ratio is 1.8. The throat area is 5
cm2. The velocity at the throat is sonic and
the diverging section acts as a nozzle. Determine the
following:
a. The mass flow
rate
b. The exit pressure and
temperature
c. The exit Mach
number
d. The exit velocity
2. The converging-diverging
nozzle now has a throat area of 100 mm2 and an exit area
of 160...
A converging–diverging nozzle is designed to generate an exit Mach number of 2. The nozzle is...
A converging–diverging nozzle is designed to generate an exit
Mach number of 2. The nozzle is supplied with air from a large
reservoir in which the pressure is kept at 6.5 MPa. Assuming
one-dimensional isentropic flow, find
a. The maximum back-pressure at which the nozzle will be
choked
b. The range of back-pressures over which there will be a shock
in the nozzle
c. The design back-pressure
d. The range of back-pressures over which there is supersonic
flow on the...
A converging-diverging nozzle is designed to operate with an exit Mach number of 2. The nozzle...
A converging-diverging nozzle is designed to operate
with an exit Mach
number of 2. The nozzle is supplied from an air reservoir at 600
kPa and temperature
is 300 K. The throat area of the nozzle is 5 cm2
.
Determine:
(a) The ratio of exit-to-throat area and exit area
(b) Given the area ratio in part (a), find the range of back
pressure over which the
nozzle is choked. What is the critical pressure and design
pressure?
Also, calculate...
A converging-diverging nozzle is designed to operate with an exit Mach number of 2. The nozzle...
A converging-diverging nozzle is designed to operate with an
exit Mach number of 2. The nozzle is supplied from an air reservoir
at 600 kPa and temperature is 300 K. The throat area of the nozzle
is 5 cm2.
Determine:
(a) The ratio of exit-to-throat area and exit area.
(b) Given the area ratio in part (a), find the range of back
pressure over which the nozzle is choked. What is the critical
pressure and design pressure?
Also, calculate the...
compressible flow: a converging-diverging nozzle has an area ratio of 5 and a stagnation pressure of...
compressible flow:
a converging-diverging nozzle has an area ratio of 5 and a
stagnation pressure of 1 MPa. Assume that the gas in the nozzle
behaves exactly like air. Which of the following most accurately
gives the range of nozzle exit pressures for which the flow is
choked, but has subsonic flow at the nozzle exit?
a)990 kPa ?? 1 MPa
b)244 kPa ?? 1 MPa
c)21 kPa ?? 1MPa
d)1 kPa ?? 1 MPa
e)244 kPa ?? 990 kPa...
Consider a converging-diverging nozzle with an exit-to-throat area of 3. The inlet reservoir pressure is 1...
Consider a converging-diverging nozzle with an exit-to-throat
area of 3. The inlet reservoir pressure is 1 atm and the exit
pressure is 0.5 atm.
(a) For this pressure ratio a normal shock will stand somewhere
inside the divergent portion of nozzle. Calculate the location of
shock (A/At =?).
(b) back pressure if the flow were isentropic throughout.
Air flows steadily through a converging-diverging nozzle with a throat area equal to 1.395 in2 ,...
Air flows steadily through a converging-diverging nozzle with a
throat area equal to 1.395 in2 , and an exit area equal to 2.79 in2
. A normal shock wave stands at the exit plane of the nozzle. The
exiting jet flows into a large room, where the pressure is equal to
14.7 psia. The temperature of the air in the exit jet stream, just
after the nozzle exit, is measured at 87 deg F. Calculate the mass
flow rate through...
Consider a rocket that burns steadily. The higher pressure in the combustion chamber, the faster the...
Consider a rocket that burns steadily. The higher pressure in
the combustion chamber, the faster the propellant burns. Why is
this? The relationship is such that the higher the pressure, the
closer the gaseous flame is to the surface and the more effectively
it can transfer heat back to the surface thereby gasifying the
propellant quicker. The rate of gas generation, ?_? , can be
described by the equation: ?_?=?_1 ?^?, where P is the pressure,
and C1 and n...
Consider a rocket that burns steadily. The higher pressure in the combustion chamber, the faster the...
Consider a rocket that burns steadily. The higher pressure in
the combustion chamber, the faster the propellant burns. Why is
this? The relationship is such that the higher the pressure, the
closer the gaseous flame is to the surface and the more effectively
it can transfer heat back to the surface thereby gasifying the
propellant quicker. The rate of gas generation, ?_? , can be
described by the equation: ?_?=?_1 ?^?, where P is the pressure,
and C1 and n...
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