A convergent–divergent nozzle with an exit area to throat area ratio of 3 is supplied with...

A convergent–divergent nozzle with an exit area to throat area ratio of 3 is supplied with air from a reservoir in which the pressure is 350 kPa. The air from the nozzle is discharged into another large reservoir. It is found that the flow leaving the nozzle exit is directed inward at an angle of 4° to the nozzle centerline. The velocity on the nozzle exit plane is supersonic. What is the pressure in the second reservoir?

Solutions

Expert Solution

samet mamat answered 1 year ago

Next > < Previous

Related Solutions

A convergent-divergent duct has a throat area that is 1/3 the area of the inlet. If...

A convergent-divergent duct has a throat area that is 1/3 the area of the inlet. If the pressure at the throat is 95lbft2 less than the pressure at the inlet, what is the inlet velocity, assuming density is .002 slugs/ft3 ?

Air is supplied to a convergent–divergent nozzle from a large tank in which the pressure and...

Air is supplied to a convergent–divergent nozzle from a large tank in which the pressure and temperature are kept at 700 kPa and 40°C, respectively. If the nozzle has an exit area that is 1.6 times the throat area and if a normal shock occurs in the nozzle at a section where the area is 1.2 times the throat area, find the pressure, temperature, and Mach number at the nozzle exit. Assume one-dimensional, isentropic flow.

Air is supplied to a convergent–divergent nozzle from a reservoir where the pressure is 100 kPa....

Air is supplied to a convergent–divergent nozzle from a reservoir where the pressure is 100 kPa. The air is then discharged through a short pipe into another reservoir where the pressure can be varied. The cross-sectional area of the pipe is twice the area of the throat of the nozzle. Friction and heat transfer may be neglected throughout the flow. If the discharge pipe has constant cross-sectional area, determine the range of static pressure in the pipe for which a...

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 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

Problem 1: Carbon dioxide flows isentropically at the rate of 1 kg/s through a convergent-divergent nozzle....

Problem 1: Carbon dioxide flows isentropically at the rate of 1 kg/s through a convergent-divergent nozzle. The stagnation temperature is 310 K and the stagnation pressure is 1400 kPa. If the exit pressure is 101.3 kPa, determine a) throat area, b) exit Mach number and c) exit velocity. Assume sonic (M =1) conditions at throat. (d) plot using MS excel variation of: total temperature, total pressure, total density, density, temperature, Mach number, velocity, speed of sound along the centre line...

Please solve fully Determine whether the geometric series is convergent or divergent. If it is convergent,...

Please solve fully Determine whether the geometric series is convergent or divergent. If it is convergent, find its sum.8 − 11 + 121 8 − 1331 64 + Step 1 To see 8 − 11 + 121 8 − 1331 64 + as a geometric series, we must express it as ∞ ar n − 1 n = 1 . For any two successive terms in the geometric series ∞ ar n − 1 n = 1 , the ratio of...

Determine whether the integrals are divergent or convergent. Calculate the convergent ones. ?)∫ 1 / ?^2+?...

Determine whether the integrals are divergent or convergent. Calculate the convergent ones. ?)∫ 1 / ?^2+? ?x (from 1 to positive infinity) ?) ∫ ? −√? / √? ?? ( from 1 to positive infinity) ?) ∫ ??????? (negative infinity to positive infinity) ?) ∫ 1 / √3−? ?x ( from 2 to 3)

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...

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...

Subjects