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Consider the incompressible flow of water through a divergent duct. The inlet velocity and area are \(5 \mathrm{ft} / \mathrm{s}\) and \(10 \mathrm{ft}^{2}\), respectively. If the exit area is 4 times the inlet area, calculate the water flow velocity at the exit.

Short Answer

Expert verified
The exit velocity is 1.25 ft/s.

Step by step solution

01

Understand the Problem

We are given the inlet velocity, the inlet area, and the fact that the exit area is 4 times the inlet area. We need to find the water flow velocity at the exit.
02

Define Known Values

Inlet velocity, \(V_1 = 5\, \text{ft/s}\); Inlet area, \(A_1 = 10\, \text{ft}^2\); Exit area, \(A_2 = 4 \times A_1 = 40\, \text{ft}^2\).
03

Apply the Continuity Equation

The continuity equation for incompressible flow states that the mass flow rate must be constant. Thus, \(A_1 V_1 = A_2 V_2\), where \(V_2\) is the exit velocity.
04

Calculate the Exit Velocity

Substitute the known values into the continuity equation: \(10\, \text{ft}^2 \times 5\, \text{ft/s} = 40\, \text{ft}^2 \times V_2\). Solve for \(V_2\):
05

Solve for \(V_2\)

\(V_2 = \frac{10 \times 5}{40} = \frac{50}{40} = 1.25\, \text{ft/s}\). The exit velocity is \(1.25\, \text{ft/s}\).

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Key Concepts

These are the key concepts you need to understand to accurately answer the question.

Incompressible Flow
Incompressible flow refers to a fluid flow condition where the fluid's density remains constant throughout the flow. This assumption simplifies the equations of fluid dynamics significantly. It is crucial to distinguish between compressible and incompressible flow, as this affects how we model and solve fluid flow problems.

For many practical engineering applications, especially involving liquids like water, the flow can be treated as incompressible. This is because liquids have very low compressibility, meaning their density doesn't change much under pressure. This assumption allows us to apply simpler equations, like the continuity equation, which relies on the conservation of mass.

Understanding incompressible flow is key to solving problems related to fluid movement in pipelines, channels, and ducts, where we need to ensure that the mass flow into a system equals the mass flow out.
Fluid Dynamics
Fluid dynamics is the study of how fluids, both liquids and gases, move and interact with their surroundings. It's a crucial field of study in physics and engineering, as it helps us understand and predict the behavior of fluid systems, from small-scale water pipes to vast atmospheric patterns.

One of the fundamental principles in fluid dynamics is the conservation of mass, which is often expressed through the continuity equation. This principle asserts that for a steady, incompressible flow, the mass flow rate at different sections of a flow system remains constant. This is why, in our exercise, we can set the product of inlet area and velocity equal to the product of exit area and velocity.

Studying fluid dynamics involves not only understanding how fluids flow, but also how they interact with solid surfaces and environments, affecting force, pressure, and energy changes in the system.
Mass Flow Rate
Mass flow rate is a measure of the amount of mass passing through a section of a system per unit time. This is a critical concept in fluid dynamics because it ensures we understand how much fluid is being transferred from one part of the system to another.

In the context of an incompressible flow, the mass flow rate is given by the product of the fluid's density, the cross-sectional area of flow, and the velocity of the fluid. Given the incompressible assumption, density remains constant, which simplifies the mass flow rate to just area times velocity.

The continuity equation, which we used to solve our exercise, is derived from the principle of a constant mass flow rate. It states \[ A_1 \times V_1 = A_2 \times V_2 \]where \( A_1 \) and \( V_1 \) are the area and velocity at the inlet, and \( A_2 \) and \( V_2 \) at the exit, respectively. Through it, we can calculate unknown velocities or areas in a flow system.

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Most popular questions from this chapter

Consider a low-speed wind tunnel (see Fig. 4.15) that is a constant width of \(2 \mathrm{~m}\) throughout its length (i.e., each cross section of the tunnel is a rectangle of width \(2 \mathrm{~m}\) ). The entrance and exit heights of the nozzle are 4 and \(0.5 \mathrm{~m}\), respectively. The airflow velocity in the test section is \(120 \mathrm{mph}\). Calculate the airflow velocity in \(\mathrm{m} / \mathrm{sec}\) at the entrance to the nozzle.

Consider an airplane flying with a velocity of \(60 \mathrm{~m} / \mathrm{s}\) at a standard altitude of \(3 \mathrm{~km}\). At a point on the wing, the airflow velocity is \(70 \mathrm{~m} / \mathrm{s}\). Calculate the pressure at this point. Assume incompressible flow.

The dynamic pressure is defined as \(q=0.5 \rho V^{2}\). For high-speed flows, where Mach number is used frequently, it is convenient to express \(q\) in terms of pressure \(p\) and Mach number \(M\) rather than \(\rho\) and \(V\). Derive an equation for \(q=q(p, M)\).

We wish to operate a low-speed subsonic wind tunnel so that the flow in the test section has a velocity of \(200 \mathrm{mi} / \mathrm{h}\). Consider two different types of wind tunnels (see figure below): \((a)\) a nozzle and a constant-area test section, where the flow at the exit of the test section simply dumps out to the surrounding atmosphere (that is, there is no diffuser); and ( \(b\) ) a conventional arrangement of nozzle, test section, and diffuser, where the flow at the exit of the diffuser dumps out to the surrounding atmosphere. For both wind tunnels \((a)\) and \((b)\), calculate the pressure differences across the entire wind tunnel required to operate them so as to have the given flow conditions in the test section. For tunnel \((a)\), the cross-sectional area of the entrance is \(20 \mathrm{ft}^{2}\), and the cross-sectional area of the test section is \(4 \mathrm{ft}^{2}\). For tunnel (b), a diffuser is added to \((a)\) with a diffuser exit area of \(18 \mathrm{ft}^{2}\). After completing your calculations, examine and compare your answers for tunnels \((a)\) and \((b)\). Which requires the smaller overall pressure difference? What does this say about the value of a diffuser in a subsonic wind tunnel?

Consider the flow of air through a supersonic nozzle. The reservoir pressure and temperature are \(5 \mathrm{~atm}\) and \(500 \mathrm{~K}\), respectively. If the Mach number at the nozzle exit is 3, calculate the exit pressure, temperature, and density.

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