30°C P.? Air 235 m/s tank 2 Mercury

Q: Calculate the ratio of kinetic energy to internal energy at a point in an airflow where the Mach…

A: We know that Mach number is the ratio of the velocity of the fluid to the velocity of sound in the…

Q: How does a siphon work? Are there any limitations (suchas how high or how low can you siphon water…

A: Siphon:  A siphon is a long bent tube that is used to carry a liquid from one tank at a lower height…

Q: We wish to design a supersonic wind tunnel that produces a Mach 2.8flow at standard sea level…

A: Given Data: The exit Mach is: Me = 2.8 The mass flow rate of air is: 1 slugs/s The expression to…

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

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Q: The upstream flow properties are T1= 280 K and V= 2000 mph. What is downstream Mach number?

A: The Mach number, M, is defined as the ratio of the actual velocity V to the sonic velocity c, M=Vc…

Q: What is the maximum pressure in the sound wave generated by a rigid door slammed to stop impulsively…

A: Given Data  Speed, V= 10 m/s Smax=10 nm  Density = 1.2 Kg/m3. ω=2πf=2π(200)=400π  rad/s

Q: A circular cylinder is fitted with two surface-mounted pressuresensors, to measure pa at θ = 1808…

A: Given data: Pressure at A, θ =180° Pressure at B, θ =105°

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: 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: A supersonic inlet is sketched below and contains an oblique shock wave followed by a normal shock…

A: Given:M1=3T1=300 KP1=101.3 KPa

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: 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: 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: In Fig.  water exits from a nozzle into atmosphericpressure of 101 kPa. If the manometer fl uid has…

A: The value of pressure in section 1 can be calculated as, From the continuity equation,

Q: derive an expression for the mass flowrate of air for a C-D nozzle arrangement operating in choked…

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Q: Air flows from a reservoir where p = 300 kPa and T = 500 K through a throat to  in Fig.  where there…

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Q: The orientation of a hole can make a difference. Considerholes A and B in Fig.  which are identical…

A: Write the relation between pressures at entry and exit points of hole B and the Mach number of hole…

Q: Air enters a convergent-divergent nozzle at a temperature of 400K and a pressure of 10 atm. The…

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Q: With the aid of diagrams, explain what are Mach waves and how they are formed.

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Q: The SR-71 Blackbird is the fastest production plane capable of reaching speeds of more than Mach 3,…

A: GivenMach no. for blackbird M=3specific heat of air R=287j/kg.kspecific heat ratio γ=1.4To…

Q: diheoat = 8 cm 1 2 Exit Po da = 18 cm Shock wave Figure 4 [Gambarajah 4] (i) Determine the Mach…

A: The nozzle is a device that has varying cross-sections, in which pressure is reduced by expansion…

Q: Q5. A duct of a friction length of fx/D = 124 is connected to a Duct reservoir. A nozzle is attached…

A: Given: Receiver pressure, Pe=103.4 kPafLD=12.4Nozzle exit area, Ae=6 cm2Nozzle inlet area, A3=9…

Q: If T = = = = ² 2 ₁ -r (4 (Ap/At) and non- Newtonian, u(r) prove that (3n+1) Umean and compare to…

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Q: Describe the general principles of dynamic fluid?

A: Fluid dynamics: It is a branch of applied science which deals with movements of fluids(liquid and…

Q: 3.4. Consider a normal shock wave in air The upstream conditions are given by M = 3; P1 = 1 atm, and…

A: Since you have posted a question with multiple subparts, we will solve the first three subparts for…

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

A: Given data Mach number = 0.35 Altitude = 30000 ft Weight = 73000 lb S = 950 ft2 AR = 5.92  CD,0 =…

Q: 7. Find the temperature of air at second level for an airplane flies at two altitudes (u, = 35°, v2…

A: Given Data V2=721 m/s   μ1=35° Mach no. Difference=0.1 Ma2=1sin35=1.7436…

Q: 2) Prove that the mass of gases (m) flowing in the convergent-divergent nozzle of an afterburning…

A: Mass flow rate= m˙M= mach number P0= Total pressure T0= Total temperature A= area γ= specific heat…

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: Consi der a shockwave with an angle of ß= 25° that impinges on a wall at point p (as shown in the…

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

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Q: A jet of alcohol strikes the vertical plate in Fig. P3.112. Aforce F ≈ 425 N is required to hold the…

A: Given: The magnitude of the required force is F=425 N. The diameter of the jet is D2= 2cm. The…

Q: An experimental scramjet aircraft is flying at an altitude of 25,000m at Mach 5. Considering it;s…

A: Given: M1 =5  delta = 5 deg P2/P1 = ?

Q: Consider a normal shock wave at sea level with the density ratio, p2/p1 = 2.67. What are the…

A: A normal shock occurs when the shock wave is perpendicular to the flow direction. If the flow is…

Q: Consider the venturi nozzle of Fig. , with D = 5 cmand d = 3 cm. Stagnation temperature is 300 K,…

A: Given one-dimensional isentropic flow of air. The problem looks sticky—sparse, scattered…

Q: To what head of air (R = 287 J · kg−1·K−1) at an absolutepressure of 101.3kPa andtemperature of 15◦C…

A: Properties of air :

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: An airplane is fl ying at 300 mi/h at 4000 m standardaltitude. As is typical, the air velocity…

A: Given data: The velocity of the jet, v1 = 300 mi/h. The altitude of the airplane, h = 4000 m.…

Q: An airplane is flying at 1500m witha speed of 45 m/s. What is the stagnation pressure measured in…

A: Write down the given value using suitable variables. Here H1 signifies the initial height of the…

Q: The converging-diverging nozzle shown in Fig. P3.22 expands and accelerates dry air to supersonic…

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Q: The converging–diverging nozzle shown in Fig. P3.22expands and accelerates dry air to supersonic…

A: Inlet Area, A1=π0.0124 Outlet Area, A2=π(0.025)24 P1=284000Pa T1=665K P2=8000Pa T2=240K V1=517m/s

Q: Investigate the velocity potential ϕ = Kxy , K = constant.Sketch the potential lines in the full xy…

A: The potential lines are represented as, ϕ = Kxy , K = constant. Hence the potential lines are…

Q: The rocket in Fig. P3.68 has a supersonic exhaust, and theexit pressure p e is not necessarily equal…

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Q: . An air tank with a nozzle has a pressure of 196.32 KPa and density of 1.9 Kg/m3. Outsic diverging…

A: P=196.32kPa=196320Paρ=1.9kg/m3Mach no throat and exit= 1 and 1.5A=0.11m2 To-Find 1) Temperature and…

Q: A typical carbon dioxide tank for a paintball gun holdsabout 12 oz of liquid CO2. The tank is fi…

A: Given: mCO2=12 ozP0=850 psiadexit=0.050 in

Q: Consider the flow past a 30° expansion corner, as sketched in the figure below. The upstream…

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

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