)Air is supplied to a converging nozzle from a large reservoir where the temperature and pressure are 400 Kand 150 kPa, respectively. At a certain cross-section where the area Is 0.01 m2, the pressure and velocity are 100 kPa and 120 ms·', respectively. Assuming adiabatic flow, find the Mach number at this cross-section and determine the mass flow rate.

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

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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: . 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: Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1…

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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: 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: A converging–diverging nozzle receives air from a tank at 100 psia and 600°R. The pressure is 28.0…

A: Dear student as per the policy i have solved first three subparts for you please post the…

Q: A supersonic converging-diverging nozzle has an exit-to-throat area ratio of 1.555. The flow at the…

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

A: Given data

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: Example 2 An air stream with a Mach number of (3.04) a pressure of (302 kPa) and a temperature of…

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Q: [5] An experimental centrifugal compressor is fitted with free-vortex guide vanes in order to reduce…

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

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Q: For a nozzle-duct system shown in Fig 2.8 with y = 1.4. The inlet conditions are po1 = 10 bar and…

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Q: Q.2. Air flows through a constant-area duct is connected to a reservoir at a temperature of 500°C…

A: Given data: The inlet temperature is T1=500 °C. The inlet Pressure is P1=500 kPa The heat loss rate…

Q: Consider the isentropic flow through a convergent-divergent nozzle with an exit-to-throat area ratio…

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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: Gas flows through a converging-diverging duct. At point "A'' the cross-sectional area is 50 [cm2]…

A: Isentropic table is used to get the solution. A1 = 50 cm2 M1 = 0.4 A2 = 40 cm2

Q: Combustion gases with k = 1.33 enter a converging nozzle at stagnation temperature and pressure of…

A: To find the lowest pressure =? Given Data  K=1.33 P0=400KPa

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

A: Find , M2 , P2 at exit

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

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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: Example: Carbon dioxide flows steadily at a mass flow rate of 3 kg/s and pressure of 1400 kPa and…

A:

Q: b. Air flows in a converging-diverging nozzle Throat from stagnation conditions at P, - 500 kPa To…

A: Given:-           P0 = 500 kPaT0 = 400 kAt = 0.01 m2Ae = 0.015  m2k = 1.4R = 287 m2/s2k

Q: In compressible flow, velocity measurements with a Pitot probe can be grossly in error if relations…

A: Given Data⇒Stagnation pressure and temprature at downstreamP02=620 KPaT02=340 KUpstream…

Q: Air enters a rectangular duct at T1 = 285 K, P1 = 390 kPa, and Ma1 = 2. Heat is transferred to the…

A: The static temperature at the inlet of the duct is T1=285 K. The inlet pressure of the duct is…

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: flow angle is measured as 15.8°. Assuming the flow is isentropic, determine the e per unit frontal…

A: Given Data:Intel pressure P1 = 1.1 bar                   Find:-Intel temperature T1 = 310k…

Q: The ratio of stagnation temperature at the exit and entry of a combustion chamber is 3.75. If the…

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Q: 1. Air (y=1.4) enters a converging-diverging nozzle from a reservoir which is at a pressure of 300…

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Q: Example 5 An airstream with Mach number of 2, a pressure of 150 KPa and a temperature of 350K enters…

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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: A large tank supplies helium through a converging-diverging nozzle to the atmosphere. Pressure in…

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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: Q.1. A uniform supersonic air flow travelling at a Mach number of 2.5 passes over a wedge which…

A: Write the expression of oblique shock angle. tanθ=2Ma12sin2β-1/tanβMa12k+cos2β+2

Q: Air enters a nozzle at 0.2 MPa, 350 K, and a stagnation velocity. Assuming isentropic flow,…

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Q: when aircraft is flying at subsonic velocity, the pressure at its nose i. e. the stagnation point is…

A: Bernoulli equation states that the sum of pressure energy , kinetic energy and potential energy and…

Q: Air enters a rectangular duct at T₁ = 300 K, P₁ = = 420 kPa, and Ma₁ = 2. Heat is transferred to the…

A: Given data as per question  T₁ = 300 K P₁ = = 420 kPa  Ma₁ = 2 Heat is transferred to the air =55…

Q: Turbomachines 4

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