supersonic nozzle is also a convergent–divergent duct, which is fed by a large reservoir at the inlet to the nozzle. In the reservoir of the nozzle, the pressure and temperature are 10 atm and 300 K, respectively. At the nozzle exit, the pressure is 1 atm.

Q: At the inlet to an axial diffuser the velocity of the approaching air is 420 m/s, the stagnation…

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Q: Air at 26 psia, 320°F, and Mach number Ma = 0.7 flows through a duct. Calculate the velocity and the…

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Q: Steam at a velocity of 60 m/s and 250°C and 7 bar absolute is expanded through a nozzle to 200 C and…

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Q: Compressed air from the compressor of a gas turbine enters the combustion chamber at T1 = 700 K, P1…

A: Given:To find:The Mach number at the duct exit.The drop in stagnation pressure.

Q: Carbon dioxide flows steadily through a varying cross-sectional-area duct such as a nozzle at a mass…

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Q: 7. An underexpanded converging-diverging nozzle has throat and exit cross-sectional areas of 0.001…

A: Given: The throat area for nozzle, At = 0.001 m2 The exit area of nozzle, A2 = 0.004235 m2 The…

Q: The compressor of a jet engine tested at sea level on a stationary test bed on a day when the…

A: Given data At atmospheric pressure and temperatureT01 = 298 KP01 = 101 kPaMass flow rate = m˙ =  15…

Q: A large tank supplies helium to a converging-diverging nozzle. The pressure and temperature in the…

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Q: Air flowing steadily in a nozzle experiences a normal shock at a Mach number of Ma = 2.6. If the…

A: Given data

Q: In a wind tunnel air enters with a velocity of 200kmph. The static pressure and temperature of the…

A: Calculating Mach number, stagnation temperature, stagnation pressure and the stagnation density on a…

Q: Air flows from a large tank where the pressure and temperature are 600 kPa and 800 K, respectively,…

A: P1=600 KpaT1=800KA2=.0005 m2P2= 100 Kpa T2T1=P2P1γ-1γT2800=1006001.4-11.4T2=479.4695 K

Q: Air at a temperature of 195oC and a pressure of 500 kPa enters a smooth insulated nozzle with an…

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Q: Air at a total pressure and temperature of 8 atm and 450 K enters a frictionless constant…

A: Given data: Total pressure at inlet, P1=8 atm and temperature at inlet, T1=450 K As the flow of air…

Q: 4- Air at stagnation pressure of 600 kpa and stagnation temperature of 530 K enters a frictionless…

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Q: Air flows isentropically through a convergent-divergent nozzle from a large reservoir where the…

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Q: .2 in a converging-diverging nozzle from an inlet velocity of 90 m/s. The inlet area is 50 cm2 and…

A: Supersonic flow is typically designed to be produced near the exit plane with a converging-diverging…

Q: 1. Air flow isentropically through a converging nozzle attached to a reservoir, where the pressure…

A: Given data P0=170 KPaT0=300 KM=0.2

Q: Consider subsonic Rayleigh flow that is accelerated to sonic velocity (Ma = 1) at the duct exit by…

A: The given subsonic Rayleigh flow is accelerated by supplying heat to the fluid flow at the duct…

Q: Air with a velocity of 150 m/s enters a nozzle at a pressure of 200 kPa and temperature of 77 °C.…

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Q: b) Air flows through a cylindrical duct at a rate of 2.3 kg/s. Friction between air and the duct and…

A: Given: For air, The mass flow rate, m = 2.3 kg/s The inlet temperature, T1 = 450 K The inlet…

Q: · Air is flowing isentropically through a converging duct which is fed from a large reservoir where…

A: T1=350 K,P1=250 kPaAC=.005 m2 ,P2=150 kPa T2T1=P2P1γ-1γT2350=1502501.4-11.4T2=302.47 KNow for…

Q: A supersonic fixed-geometry inlet is operating at sea level where the temperature and pressure are…

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Q: A jet engine is to be designed for an altitude of 12,000 m, where the atmospheric pressure is 19.3…

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Q: Air flows through a constant area combustion chamber that has a diameter of 0.15 m and a length 5 m.…

A: D=.15 mL= 5m P0=1.4 Mpa T0=335 KM1=.55

Q: verging-diverging nozzle of ave occurs at the exit plane

A: Determine the value of pressure and temperature before the shock.

Q: Air flows through a long, isentropic nozzle. The temp. and pressure at the reservoir are 1000 K and…

A: Given that: Nozzle is isentropic i.e. change in entropy is zero. Temperature of air at entrance = T…

Q: A converging -diverging nozzle with a throat area of 0.0052 m^2 is attached to a very large tank of…

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Q: 3. A converging-diverging nozzle is designed to operate isentropically with air at an exit Mach…

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Q: Air in a large tank is at a pressure of 800 kPa and a temperature of 300 K. It is expanded through a…

A: Given,  Inlet pressure to the convergent-divergent nozzle is, P0=800 kPa Inlet temperature to the…

Q: 1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. Just upstream of a shock wave, the air temperature and…

A: Given Data: Upstream temperature is T1 = 288 K. Upstream pressure is P1 = 1 atm. Downstream…

Q: 1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. Consider the isentropic flow through a supersonic wind-tunnel…

A: Given Data Reservoir Properties  T0=500K    and P0=10atm Nozzle exit pressure P=1atm  Adiabatic…

Q: A converging nozzle is fed with air from a large reservoir where the temperature and pressure are…

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Q: Q6/ Air is he of heat transf velocity and Disregarding static pressur

A: Given data Amount of heat transfer = 60kJ/kg Velocity of air V2=620 m/sec static pressure P2=270 kPa…

Q: D5. A converging-diverging nozzle operates with air and subsonic flow at the inlet and supersonic…

A: Find , M2 , P2 at exit

Q: A flow of air with Mach number M1 = 2, pressure p1 = 0.7 atm, and temperature 630 deg R is turned…

A: The data given is, δ=26.38° M1=2 P1=0.7 atm T1=630°R

Q: 1. Air is flowing isentropically through a converging duct which is fed from a large reservoir where…

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Q: A converging duct is fed with air from a large reservoir where the temperature and pressure are 400…

A: Given,  Temperature of air , To = 400 K Pressure of air , Po = 200 KP

Q: An air stream with a Mach number of (3.04) a pressure of (302 kPa) and a temperature of (502 K)…

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Q: Consider supersonic flow of air through a 7-cm-diameter duct with negligible friction. Air enters…

A: Given Data Properties of air  R = 0.287 Kj/Kg-K CP = 1.005 Kj/Kg-K K=1.4 Inlet condition Ma1 = 1.8,…

Q: An ideal gas is to flow isentropically from a large tank where the air is maintained at a tempera…

A: Since you have posted a question with multiple sub-parts, we will provide the solution only to the…

Q: 1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. In the reservoir of a supersonic wind tunnel, the velocity is…

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