Question

In: Mechanical Engineering

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 nozzle exit plane

Solutions

Expert Solution

samet mamat answered 2 years ago
Next > < Previous

Related Solutions

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...
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.
A C-D nozzle is to be designed to produce a flight Mach number of 3.0 for...
A C-D nozzle is to be designed to produce a flight Mach number of 3.0 for the atmospheric conditions (pressure and temperature) at 15 km altitude in the test section of a supersonic wind tunnel. The diameter of the test section is 10 cm. Assume the gas has Y(gamma) = 1.4 and R = 2.077 kJ/kg*K, determine (a) the mass flow rate that must be provided, (b) the nozzle throat area, (c) the reservoir temperature and (d) the reservoir pressure.
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
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...
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...
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...
Calculate the variation with Tt4 of exit Mach number, exit velocity, specific thrust. Fuel/air ratio, and...
Calculate the variation with Tt4 of exit Mach number, exit velocity, specific thrust. Fuel/air ratio, and thrust specific fuel consumption of an ideal turbojet engine for compressor pressure ratios of 10 and 20 at a flight Mach number of 2 and T0= 217K.Perform calculations at Tt4 values of 2400K, 2200K, 2000K and 1800K. Use hPR= 42,800kJ/kg, cp= 1.004kJ/kg and γ= 1.4.
A nozzle is is designed to achieve M=4 under expanded exit flow conditions. For the given...
A nozzle is is designed to achieve M=4 under expanded exit flow conditions. For the given total pressure and total temperature, calcuate: a) exit Mach b)mach at which normal shock occurs in the model
ADVERTISEMENT
Subjects
ADVERTISEMENT
Latest Questions
ADVERTISEMENT