14 cm? Air at 10 cm? 100°C Shock Sea-level air

Q: A convergent-divergent nozzle with throat area of 35cm². At a point downstream of the throat area,…

A: Nozzle type= Convergent-Divergent nozzle Area of throat Ao= 35 cm2 V1 = 155 m/s T1 = 330K P1 =…

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

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Q: Air at 800 kPa and 1200 K enters a converging nozzle with negligible velocity (i.e., these are…

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Q: ir, at stagnation conditions of 450 K and 250 kPa, flows through a nozzle. At section 1, where the…

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Q: Q2 (a) In designing a nozzle why nozzle angle is not zero. Explain with the help of sketch. Q2 (b)…

A: Nozzle :- Nozzle is an device which are used to increase the kinetic energy and convert in to heat.…

Q: Prablen (t A large VacuuM tank, hetdat 6okAt abslute, Sucke searlevel standard qir throngh f…

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Q: An airplane uses a pitot-static tube as a velocimeter. Themeasurements, with their uncertainties,…

A: Given data: Static temperature, T = - 110C = 262 K Static pressure, P = 60 kPa Pressure difference ,…

Q: A normoa shock wave exists in air flow with up stream M=2 and a pressure of 20kpa and temperature of…

A: Given: Upstressm properties: Mx=2Px=20kPaTx=15°C or 288K Solution: Downstream mach number is given…

Q: JI Air stream flow in a convergent - divergent nozzle, with a stagnation pressure of 120 kPa, the…

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Q: Q3: Uniform flow at Mach number equal (2) passes over a wedge of 10 half-angle, find M2, P2/P1,…

A: This problem is related to fluid mechanics. Fluid mechanics is the subject of mechanical engineering…

Q: Air flows at high speed through a Herschel venturi monitoredby a mercury manometer, as shown in Fig.…

A: Given data, Determine the density of fluid by using the ideal gas equation,

Q: 26 (a) Explain briefly the difference between incompressible and compressible fluid flow.

A: Compressible and incompressible flow will be defined based upon density of fluid due to application…

Q: The tank is filled with air at 20°C and 139 Pa at rest. Tooth from a nozzle under stable weather…

A: I apologize for not giving the answer only as I am required to give some explanation. i will try to…

Q: A gas, assumed ideal, flows isentropically from point 1,where the velocity is negligible, the…

A: Hello. Since your question has multiple sub-parts, we will solve first three sub-parts for you. If…

Q: Figure  shows the exit of a converging–diverging nozzle,where an oblique shock pattern is formed. In…

A: Hello. Since your question has multiple sub-parts, we will solve the first three sub-parts for you.…

Q: : Air flows from a reservoir maintained at 25 °C and 5 bar. It flows through a vith throat and exit…

A: Given:temperature, T=25o Creservoir pressure, P1=5 barthroat diameter, dt=5 cmexit diameter, de=10…

Q: The Mach no. of a fixed geometry inlet at overspeeded for starting mode (Ai= 0.13 m2, At= 0.095 m2

A: Inlet Area, Ai = 0.13 m2 Throat Area, At = 0.095 m2

Q: diverging nozzle. The air has tota Scm, M=0.8 and V =300 m/s. det (for air tal

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Q: If the exit Mach number in Fig. is 2.2, what is theexit area?(a) 0.10 m2, (b) 0.12 m2, (c) 0.15 m2,…

A: Write the given data.

Q: Air, assumed to be an ideal gas with k = 1.40, fl ows isentropicallythrough a nozzle. At section 1,…

A: Given data: The temperature at the section 2 is, T2 = -50 0 The ratio of specific heat is, k =…

Q: Supersonic air takes a 5° compression turn, as inFig. . Compute the downstream pressure and…

A: Write the given information.

Q: When operating at design conditions (smooth exit to sealevelpressure), a rocket engine has a thrust…

A: Write the given data.

Q: Air flows through a normal shock wave, upstream conditions are V₁= 650 m To1= 550 k and po₁= 750…

A: First of all what is stagnation properties? The isentropic stagnation state is defined as the state…

Q: What is the area where the shock appears? Calculate (b) the pressure and (c) the temperature…

A: Given DataThe reservoir temperature of air T0= 350KThe reservoir pressure of air P0= 500 KP aThe…

Q: a) A convergent nozzle with a given area ratio is supplied with air at a constant stagnation…

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Q: /2 Air flows from a reservoir where Pa and T-500 K through a throat to section 1 P =300 Figure where…

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Q: The scramjet of Fig.  operates with supersonic fl owthroughout. Assume that the heat addition of 500…

A: Given that, Heat addition between section 2 and 3, Q=500 kJ/kgArea between section 2 & 3, A=0.2…

Q: he entropy change across a normal shock wave (Tox= 505 K, vx= 490 ms-1)

A: Given data: Tox = 505 K Vx = 490 m/s For air, specific heat, cp = 1.005 kJ/kg.K = 1005 /kg.K Gas…

Q: 1. Air, with stagnation conditions of 800 kPa and 100 °C, ex pands isentropically to a section of a…

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Q: Q4: : The pressure ratio across a normal shock wave that occurs in air is 1.4. A head of the shock…

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Q: A flow with Mach number M1 = 2 and pressure p1 = 1 atm is turned away from itself twice, first…

A: The diagram for first flow with two turns,

Q: Q: Helium, in a large tank at 100 °C and 400 kPa, discharges to a receiver through a…

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Q: ch no. of the throat in an isentropic converging-diverging nozzle (po= 140 kPa, To= 350 K, mo= 1…

A: We have to calculate mach number at the throat

Q: How do the compressible pipe flow formulas behave forsmall pressure drops? Let air at 20°C enter a…

A: Given: The temperature of the air at the entry of the tube is T1 = 20 oC. The friction coefficient…

Q: What is the atmospheric pressure? kPa Required informetion Ar in a tank at 120 kPa and 300 K…

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Q: Q1// Air stream flow in a convergent- divergent nozzle, with a stagnation pressure of 120 kPa, the…

A: The nozzle is both convergent and divergent. The forward section of the nozzle is convergent,…

Q: Q1: Air expands from a storage tank through a converging diverging nozzle having a hroat area of (70…

A: Given:The throat area is .The shock area is .The exit area is .The pressure and temperature is  and…

Q: At the exit of Converging nazzle theair velocitywas 273m1s Find mach bumber at this section and the…

A: At the exit of converging nozzle the air velocity was 273m/s ,Find Mach number a this section…

Q: Q3:/ A large reservoir at (600 k) supplies air flow through a converging-diverging duct with throat…

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Q: Q2: Air flows isentropically through converging nozzle which has a throat of 7 cm?. The stagnation…

A: Given data: -  The throat area of the nozzle is A = 7 cm2. The stagnation pressure is Po = 130 kPa.…

Q: A uniform supersonic flow of air at Mach 3.8, with a stagnation pressure of 5.0 MPa and stagnation…

A: Given Data: M1 = 3.8 P = 5Mpa T = 1100K v2-v1 = 23o To find: 1) Downstream Mach 2) Downstream…

Q: A large room uses a fan to draw in atmospheric air at 20°Cthrough a 30-cm by 30-cm commercial-steel…

A: (a) The density of the air is: ρair=1.2kgm3 For commercial steel, ε=0.046 mm Side length, DH=30 cm…

Q: Q4. ajExplane the magnus effect in the potential fow b) A cylinder woith 50 cm in length, is under…

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Q: If there are no shock waves and the pressure at one ductsection in Fig.  is 55.5 kPa, what is the…

A: given data as per the question The temperature of tank =400 k The pressure of tank =300 Kpa…

Q: Q1: Air enters a converging-diverging nozzle having throat diameter of 8.5cm and exit diameter 28cm.…

A: Given,  Throat diameter, dT=8.5cm=0.085 m Exit diameter, dE=28cm=0.28m The cross-sectional area of…