A converging–diverging nozzle receives air from a tank at 100 psia and 600°R. The pressure is 28.0 psia immediately preceding a plane shock that is located in the di- verging section. The Mach number at the exit is 0.5 and the flow rate is 10 lbm/sec. Determine: (a) The throat area. (b) The area at which the shock is located. (c) The outlet pressure required to operate the nozzle in the manner described abov

Q: Q.4. Air is fed from a large reservoir, where the temperature and pressure are 280 K and 300 kPa…

A: Given: Converging diverging nozzle with shock at the exit P0=300 kPa; T0=280 K  D*=0.1 m; De=0.15 m…

Q: Problem 5. Air flows steadily and adiabatically from a large tank at a stagnation pressure of Poi =…

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Q: Q.4. Air is fed from a large reservoir, where the temperature and pressure are 280 K and 300 kPa…

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Q: n aircraft is flying at an altitude of 12000 metres (T= 216.65 K. p = 0.193 bar) at a Mach number of…

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Q: A normal shock produced by an explosion propagate at a constant velocity of 450 m/s into still air…

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Q: A steady one-dimensional isentropic flow in variable area passages is called “variable area flow”.…

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

A: Since you have asked multiple questions in a single request, we would be answering only the first…

Q: A gas initially at a subsonic velocity enters an adiabatic diverging duct. Discuss how this affects…

A: (a) When a gas is flowing at the subsonic velocity and passed through a diverging duct, its velocity…

Q: How does the normal shock affect (a) the fluid velocity, (b) the static temperature, (c) the…

A: Effect of normal shock can on: Part (a): The velocity of fluid decreases with the application of…

Q: n For isentropic air flowing through a converging-diverging nozzle, complete the tences below using…

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Q: For unchoked c-d nozzle, the -i supersonic flow through the :diverging part can be attained by…

A: as per our guideline, I am giving the answer to 1st question. if you want a solution to another…

Q: Air enters a compressor at a stagnation state of 100 kPa and 27 ∘C. If it has to be compressed to a…

A: Data given-  P1 = 100 kPa  T1 = 27°C = 300 K  P2 = 900 KPa  m = 0.02 kg/s  Process is isentropic {…

Q: Can a shock wave develop in the converging section of a converging–diverging nozzle? Explain.

A: In order to produce a shock wave, the flow must be a supersonic flow. Supersonic flow: The velocity…

Q: Air enters a converging–diverging nozzle, as shown at 1.0 MPa and 800 K with negligible velocity.…

A: Given data

Q: 1- For unchoked c-d nozzle, the supersonic flow through the diverging part can be attained by:…

A: 1. c ans Notwithstanding, for the supersonic stream, this conduct is turned around, and expanding…

Q: Air is driven from a reservoir at 1.3 MPa through a converging-diverging nozzle with a design Mach…

A: As per BARTLEBY rule i answer only first 3 parts (a,b,c),so i hope you understand.

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

A: We are suppose to solve only one question. Please post other question as a separate question.

Q: Air enters a compressor with a stagnation pressure of 100 kPa and a stagnation temperature of 35°C,…

A: Given: The initial stagnation pressure of the air is P1=100 kPa. The final stagnation pressure of…

Q: Inlet stagnation air pressure of a two-dimensional compressor cascade is 1.0 bar and inlet…

A: Inlet stagnation air pressure = 1.0 barInlet stagnation temperature = 295 KInlet Mach Number =…

Q: The stagnation pressure across ,a normal shock wave is always poy ≥ pox O poy = pox O poy pox O

A: Option: is correct  poy < pox Because across the normal shock wave the stagnation pressure…

Q: A centrifugal compressor has an impeller tip speed of 360 m/s. Determine the absolute Mach number of…

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Q: What would happen if we tried to further accelerate a supersonic fluid with a diverging diffuser?

A: When the supersonic fluid is accelerated through the divergent diffuser the pressure will decrease…

Q: Inlet stagnation air pressure of a two-dimensional compressor cascade is 1.1 bar and inlet…

A: dear student please rate me p  stagnation air pressure = 1.1 bar Inlet stagnation temperature = 310…

Q: The stagnation pressure after the normal shock wave in a diverging nozzle (pi= 170 kPa, ,Mi= 2.4,…

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

A: Find , M2 , P2 at exit

Q: b) Air enters a converging-diverging nozzle at 900 kPa and 427 °C with negligible velocity. The mass…

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Q: Consider subsonic Fanno flow accelerated to sonic velocity (Ma = 1) at the duct exit as a result of…

A: Given, Initially, the flow is the subsonic flow. The Mach number for Sub-sonic flow is less than…

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

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Q: Consider a converging nozzle and a converging– diverging nozzle having the same throat areas. For…

A: For Converging and converging diverging nozzle the mass flow rates are equal at the sonic…

Q: Q9: A normal shock wave is propagated into still air with a velocity of 722.4 m/s. The still air…

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Q: A gas initially at a subsonic velocity enters an adiabatic converging duct. Discuss how this affects…

A: (a). The velocity of the gas decreases.

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

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

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Q: Hydrogen entering a supersonic nozzle at 450 m/s. The inlet conditions are 10 kPa and 450 °C. The…

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

A: INTRODUCTION: In this task, we will compute the Mach number and the mass flow rate. The Mach number…

Q: Is it possible to accelerate a fluid to supersonic velocities with a velocity other than the sonic…

A: Given Supersonic velocities To find Acceleration of a fluid to supersonic velocities with a velocity…

Q: Consider a converging nozzle with a low velocity at the inlet and sonic velocity at the exit plane.…

A: A converging nozzle with a low velocity at the inlet and sonic velocity at the exit plane. now the…

Q: Consider subsonic Fanno flow of air with an inlet Mach number of 0.70. If the Mach number increases…

A: (a) The stagnation temperature during the Fanno flow process remains constant because the heat and…

Q: QUESTION 6 Air enters a diffuser with an averaged velocity of 360 m/s at a temperature of 340 kPa…

A: Given Information :Inlet velocity of the diffuser is V1 = 360 m/sStagnation pressure at the inlet…

Q: What will happen to the entropy of a flow across a shock? O It will stay the same O It will decrease…

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Q: Air enters a converging–diverging nozzle with low velocity at 2.4 MPa and 120°C. If the exit area of…

A: Given Data⇒At EntranceP1=2.4 MPaT1=120°CProblem definition⇒Problem says estimate backpressure.

Q: abcdefghikimnopqrstuvwxyz abcdefghjklmnopqrstuvwxyz abcdefghijklmnop yz A converging nozzle has a…

A: