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Chapter 11: Problem 1

Distinguish between flow of an ideal gas and inviscid flow of a fluid.

Short Answer

Expert verified
Ideal gas flow, governed by the ideal gas law, considers particles with no interaction except during elastic collisions, and the flow can change due to variations in temperature, pressure, and volume. Inviscid fluid flow refers to a zero-viscosity fluid with no internal frictional forces between different fluid layers, governed by Euler's equations. Its flow is not affected by shear stress or friction.

Step by step solution

01

Define Ideal Gas

An ideal gas is a theoretical gas composed of particles on a lattice site, with no interaction except for completely elastic collision. The ideal gas law governs its behavior, PV=nRT, where P is pressure, V is volume, n is the number of moles, R is the ideal gas constant, and T is the temperature.
02

Define Inviscid Flow

Inviscid flow refers to the flow of a fluid with zero viscosity. In other words, there are no internal frictional forces between different layers of the fluid while it's in motion. This is also a theoretical concept, as all real fluids have some viscosity. The Euler's equations govern the flow of inviscid fluids.
03

Compare

The flow of an ideal gas can change due to variations in temperature, pressure, and volume, while the inviscid fluid flow is not affected by any shear stress or friction due to its zero viscosity nature. Ideal gas molecules are considered to have no size and do not interact with each other except during elastic collisions, while inviscid fluid flow does not consider the interaction forces between liquid molecules.

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Most popular questions from this chapter

The flow blockage associated with the use of an intrusive probe can be important. Determine the percentage increase in section velocity corresponding to a \(0.5 \%\) reduction in flow area due to probe blockage for airflow if the section area is \(1.0 \mathrm{m}^{2}, T_{0}=\) \(20^{\circ} \mathrm{C},\) and the unblocked flow Mach numbers are (a) \(\mathrm{Ma}=0.2\) (b) \(\mathrm{Ma}=0.8\) (c) \(\mathrm{Ma}=1.5,(\mathrm{d}) \mathrm{Ma}=30\)

A normal shock occurs in a stream of oxygen. The oxygen flows at \(\mathrm{Ma}=1.8\) and the upstream pressure and temperature are 15 psia and \(85^{\circ} \mathrm{F}\) (a) Calculate the following on the downstream side of the shock: static pressure, stagnation pressure, static temperature, stagnation temperature, static density, and velocity. (b) If the Mach number is doubled to \(3.6,\) what will be the resulting values of the parameters listed in part (b)?

Air is supplied to a convergent-divergent nozzle from a reservoir where the pressure is \(100 \mathrm{kPa}\). The air is then discharged through a short pipe into another reservoir where the pressure can be varied. The cross- sectional area of the pipe is twice the area of the throat of the nozzle. Friction and heat transfer may be neglected throughout the flow. If the discharge pipe anstant cross-sectional area, determine the range of static pressure in the pipe for which a normal shock will stand in the divergent section of the nozzle. If the discharge pipe tapers so that its cross- sectional area is reduced by \(25 \%\), show that a normal shock cannot be drawn to the end of the divergent section of the nozzle. Find the maximum strength of shock (as expressed by the upstream Mach number) that can be formed.

Show that for Rayleigh flow, the maximum amount of heat that may be added to the gas is given by: \\[\frac{q_{\max }}{c_{p} T_{1}}=\frac{\left(\mathrm{Ma}_{1}^{2}-1\right)^{2}}{2(k+1) \mathrm{Ma}_{1}^{2}}\\]

Standard atmospheric air \(\left(T_{0}=59^{\circ} \mathrm{F}, p_{0}=14.7 \mathrm{psia}\right)\) is drawn steadily through a frictionless and adiabatic converging nozzle into an adiabatic, constant cross-sectional area duct. The duct is \(10 \mathrm{ft}\) long and has an inside diameter of \(0.5 \mathrm{ft}\). The average friction factor for the duct may be estimated as being equal to \(0.03 .\) What is the maximum mass flowrate in slugs/s through the duct? For this maximum flowrate, determine the valies of static temperature, static pressure, stagnation temperature, stagnation pressure, and velocity at the inlet [section (1)] and exit [section (2)] of the constant area duct. Sketch a temperature-entropy diagram for this flow.
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