ISA 1932 Conical nozzle shape diffuser Throat tap 1es 15° 0.7d 2 Flow (c)

Q: Air at 550 kPa and 100°C enters a smooth 1-m-long pipeand then passes through a second smooth pipe…

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Q: b) A soda straw is 20 cm long and 2 mm in diameter. It delivers cold cola, approximated as water at…

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Q: Air flows through a rough pipe 120 ft long and 3 in indiameter. Entrance conditions are p = 90…

A: Write the properties of the specific heat ratio of air. Write the expression of the temperature at…

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 air tank of volume 1.5 m3 is initially at 800 kPa and20 °C. At t = 0, it begins exhausting…

A: Given data

Q: Air at 20 °C and 1 atm flows past a smooth flat plate at Uoo =20.1 m/s (below figure). A pitot…

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Q: Downstream of a normal shock wave, in airflow, the conditionsare T2 = 603 K, V2= 222 m/s, and p2 =…

A: Given that, Mach Number at state 2 will be calculated as follows,

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

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Q: Consider the Gulfstream IV flying at Mach = 0.8 at an altitude with atmospheric pressure of…

A: Given data Mach number of aircraft = 0.8 Weight = 73000 lb S = 950 ft2 AR = 5.92 CD,0 = 0.015 K =…

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: Helium, at T0 = 400 K, enters a nozzle isentropically. Atsection 1, where A1 = 0.1 m2, a…

A: The adiabatic index for Helium is 1.66 and the characteristic gas constant is 2077 J/kg.k, (a) The…

Q: An explosion in air, k = 1.4, creates a spherical shock wave propagating radially into still air at…

A: (a) Calculate the Mach number. p2p1=1+2γγ+1M2-11400101.3=1+21.41.4+1M2-1M=3.4625

Q: Consider the Gulfstream IV flying at Mach = 0.35. Calculate thrust required given an altitude of…

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Q: Consider the Gulfstream IV flying at Mach = 0.8 at an altitude with atmospheric pressure of…

A: Given data Speed of aircraft = 0.8 Mach Altitude Pressure = 33283.40 Pa Weight = 73000 lb = 33112.24…

Q: Air, at stagnation conditions of 500 K and 200 kPa, flows through a nozzle. At section 1, where the…

A: The Answer is Below

Q: Compressible laminar fl ow, f≈ 64/Re, may occur in capillarytubes. Consider air, at stagnation…

A: Given data: *The stagnation temperature of the air is T=100°C. *The stagnation pressure of the air…

Q: Air at 20°C and 1 atm flow at 20 m/s past the flat platein Fig. . A pitot stagnation tube, placed 2…

A: The properties of air at 20 degrees Celsius are: The manometric head in terms of air column can be…

Q: Carbon dioxide flows through an insulated pipe 25 m longand 8 cm in diameter. The friction factor is…

A: Given: The length of the pipe, L = 25 cm = 0.25 m The diameter of the pipe, d = 8 cm =0.08 m The…

Q: It is desired to pump ethanol at 20°C through 115 m of straight smooth tubing under laminar-flow…

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

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Q: In Fig.  water exits from a nozzle into atmosphericpressure of 101 kPa. If the fl ow rate is 160…

A: The flow rate of the water is From the continuity equation,

Q: The supersonic nozzle of Fig. P9.138 is overexpanded (case G of Fig. 9.12) with Ae/At= 3.0 and a…

A: Area ratio = 3 Stagnation pressure = 350 KPa Angle = 4o

Q: Water at 20 ° C flows steadily through a reducing pipe bend,as in Fig. P3.77. Known conditions are p…

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Q: At a section upstream of the throat of a converging-diverging nozzle, the air flow conditions are: T…

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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: The back pressure of the worst operating condition of a fixed geometry wind tunnel (pox= 120 kPa,…

A: Given data: pox=120 kPaAnt=0.9 m2Aduct=1.5 m2Ae=1.9 m2 Need to determine the back pressure of the…

Q: Air, at stagnation conditions of 450 K and 250 kPa, fl owsthrough a nozzle. At section 1, where the…

A: Given data To determine the Mach number and the stagnation pressure just downstream of the shock.

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

A: Given data,Inlet pressure PI=800kPaInlet temprature Ti=1200KInlet velocity is negligibleStagnation…

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

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Q: Falcon 9 rocket engine, fuel mixture LOX/RP1 is combusted in a large tank and exhausts through a…

A: PExit = 101325 (1 – H x 2.25577 x 10-5)5.25588 Here H=20km PExit = 101325 (1 – 20 x 2.25577 x…

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: A large tank, at 500 K and 200 kPa, supplies isentropicairfl ow to a nozzle. At section 1, the…

A: Given

Q: Air flows from a tank through a nozzle into the standardatmosphere, as in Fig.  A normal shock…

A: Given data as per the question Area of throat =10 cm2 Area at exit =14 cm2 The temperature of air…

Q: A uniform water stream, U∞ = 20 m/s and ρ = 998 kg/m3,combines with a source at the origin to form a…

A: Ans(b) To find out the source strength apply Bernoulli's equation…

Q: Air flows isentropically in a converging-divergingnozzle with a throat area of 3 cm2. At section 1,…

A: Given: Throat area A=3 cm2P1=101 kPaT1=300 KV1=868 m/s To determine: Whether the flow is choked or…

Q: When an oblique shock strikes a solid wall, it reflects as ashock of sufficient strength to cause…

A: Given, Ma1 = 2.5 β1 = 40o p1 = 100 kPa

Q: Problem (1): A large vacuum tank, held at sokf -absolute. Suck, sea-level standard air through a…

A: Given Data The pressure inside the tank is: P2=60 kPa The nozzle throat diameter is: d=3 cm=0.03 m…

Q: A jet of alcohol strikes the vertical plates shown in the Figure 2. A force F=425 N is required to…

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Q: (6) The coefficient of discharge for a real nozzle (Theoretical mass flux= 639.8 kgs-1m-2, To= 510…

A: Option is D  => 0.92 is the coefficient of Discharge

Q: Water at 40°C flows horizontally through a constriction similar to that in Fig. S5.9 when the…

A: Given: Pressure P1=35kPaAtmospheric pressure Patm=715mmHgDiameter D1=0.5mDiameter D2=0.15mSpecific…

Q: A converging–diverging nozzle exits smoothly to sealevelstandard atmosphere. It is supplied by a…

A: Given:Volume of tank,V=40m3Initial pressure of tank,Pi=800KPaInitial temperature of…

Q: A radial flow reaction turbine has the following characteristics: Circumferential area at entrance…

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Q: The open jet of water at 20°C exits a nozzle into sea-level air and strikes a stagnation tube as…

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Q: A blower supplies standard air to a plenum that feeds twohorizontal square sheet-metal ducts with…

A: Consider all units in British.  This question is solved with the help of energy equations.  As we…

Q: A large reservoir at 20 °C and 800 kPa is used to fill a smallinsulated tank through a…

A: Given: throat area = 1 cm2 exit area = 1.66 cm2 volume= 1 m3 To determine: (a) Elapsed time when…

Q: Air flows at high speed through a Herschel venturi monitored by a mercury manometer, as shown in…

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Q: Supersonic airflow takes a 5° expansion turn, as inFig.  Compute the downstream Mach number…

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