Consider a converging nozzle with a low velocity at the inlet and sonic velocity at the exit plane. Now the nozzle exit diameter is reduced by half while the nozzle inlet temperature and pressure are maintained the same. The nozzle exit velocity will (a) remain the same (b) double (c) quadruple (d ) go down by half (e) go down by one-fourth

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: How much work does the turbine produce for a unit kg of air?

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

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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: What is the characteristic aspect of Rayleigh flow? What are the main assumptions associated with…

A: Characteristics: Rayleigh flow is considered as frictionless, i.e., there is no relative resistance…

Q: b) Air entering a converging-diverging nozzle at 1 MPa and 527 °C with negligible velocity…

A: To = 527 +273 = 800K Po = 1 MPa  Mass flow rate = 2.86 kg/s

Q: 5- An aircraft is flying at an altitude of (12000 m) (T = 216.65 k, P = 0.193bar) at a Mach number…

A: Given data: The altitude of aircraft can be given as h = 12000 m The temperature at the given…

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: 5- An aircraft is flying at an altitude of (12000 m) (T = 216.65 k, P = 0.193bar) at a Mach number…

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Q: A convergent-divergent nozzle with an exit-to-throat area ratio of 1.616has exit and reservoir…

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Q: Argon gas is approaching a converging–diverging nozzle with a low velocity at 20°C and 150 kPa, and…

A: The mass flow rate at the throat can be expressed as, From the ideal gas relation,

Q: A fan is used to transport CO2 gas (MW = 44 g/mol) gas at rest @ 700mmHg. At the discharge end, the…

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

A: In the case of gas with supersonic velocity passing through a converging duct (adiabatic), there is…

Q: Consider a converging nozzle with sonic speed at the exit plane. Now the nozzle exit area is reduced…

A: Maximum mach number that can be achieved in a converging nozzle is unity, unless there is any…

Q: In a fixed-geometry wind tunnel, air is drawn in by means of a fan. In the supply reservoir, the…

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Q: abcdefghjklmnopqrstuvwxyz abcdefghijkimnopqrstuvwxyz abcdefghijklmnop xyz A converging nozzle has a…

A: (a) Write the given data. Athroat=8.5×10-4 m2Pstag=185 kPaTstag=450 Kk=1.4

Q: Air (y = 1.4 and R = 0.287 kJ/kg· K) enters a constant-area insulated duct with a Mach number of…

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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: onsider a converging nozzle, with exit air velocity of Ma=1.

A: We have  a converging nozzle, with exit air velocity of Ma=1.

Q: An aircraft flies with a Mach number Ma1 = 0.9 at an altitude of 7000 m where the pressure is 41.1…

A: The stagnation properties of the aircraft are found out,…

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

A: Part (a) The relation between change in velocity and the change in the area comprising Mach number…

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: Hot air enters a nozzle at pressure of 200 kPa and temperature of 700°C with a velocity of 70 m/s,…

A: Given data:

Q: Is it possible to accelerate a gas to a supersonic velocity in a converging nozzle? Explain

A: We have a standard equation, dAA=dpρV21-M2 The above equation is both for nozzle and diffuser, For a…

Q: Air at 200 kPa, 100°C, and Mach number Ma = 0.8 lows through a duct. Calculate the velocity and the…

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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: An axial flow compressor is required to deliver 50 kg/s of air at a stagnation pressure of 500 kPa.…

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Q: Q.1. Air flow adiabatically in a constant area duct. At the inlet of the duct, the Mach number,…

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Q: Air enters aa adiabatic nozzle at h1 = 200 kJ/kg and v1 = 25 m/s and exits at h2 = 100 kJ/kg, What…

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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: On a T-s diagram of Fanno flow, what do the points on the Fanno line represent?

A: Fanno flow: Fanno flow flows through the duct in which the friction forces are taken into…

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 flows steadily adiabatically through a pipe with a cross-sectional of 0.002 m. At the inlet of…

A:

Q: Atmospheric air at 101kPa and 20OC is drawn isentropically through a convergent–divergent nozzle of…

A: As given that at inlet of C-D nozzle :P1= 101kPa, T1=200°C 473 K , A2=0.033 m2 , P2=32 kPa; As the…

Q: (7) The mass flow rate from a converging-diverging nozzle (Ae= 0.02 m2, po= 200 kPa, To= 345 K, pb=…

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Q: Products of combustion enter a gas turbine with a stagnation pressure of 0.90 MPa and a stagnation…

A: k = 1.33 R = 0.287 kJ/kg·K Calculate the power output of the turbine per unit mass flow…

Q: Consider gas flow through a converging nozzle with specified inlet conditions. We know that the…

A: The gas flowing through a converging nozzle with the inlet conditions which are specified can only…

Q: The velocity at exit of an isentropic converging-diverging nozzle working at design condition (Ae=…

A: Velocity at exit is 872.14 m/s.

Q: Air (y = 1.4 and R = 0.287 kJ/kg · K) enters a constant-area insulated duct with a Mach number of…

A: Stagnation Point: The point at which the velocity of the flow is zero is known as the stagnation…

Q: (a) the exit temperature and,

A: P1=380kPaT1=450KV1=55m/sMa2=0.8k=1.4c=1.005kJ/kgKR=0.287 kJ/kgK To-Find:- a Exit temperatureb Rate…

Q: An aircraft is cruising in still air at 5°C at a velocity of 400 m/s. The air temperature at the…

A: given: velocity of aircraft at 5 C=400m/s

Q: Air at 900 kPa and 400 K enters a converging nozzle with a negligible velocity. The throat area of…

A: Find out the critical pressure  P*=P2k+1k/(k-1)=90021.4+11.4/1.4+1=475Kpa Pb<475Kpa  and…

Q: Show that the point of maximum entropy on the Fanno line for the adiabatic steady flow of a fluid in…

A: Fanno flow: An one dimensional adiabatic flow through a constant area duct with friction is called…