This document contains 23 figures related to thermodynamics of high-speed gas flow. The figures illustrate concepts such as steady flow through a duct, stagnation processes, propagation of pressure waves, variations in properties for subsonic and supersonic flows, nozzle geometry and flow, effects of back pressure, normal shock waves, irreversible versus isentropic flows, and diffuser efficiency. The document appears to be from a chapter on thermodynamics of high-speed gas flow in a textbook.

1. CHAPTER
16
Thermodynamics of
High-Speed Gas Flow

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FIGURE 16-1
Steady flow of a fluid
through an adiabatic
duct.
16-1

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FIGURE 16-3
The actual state, actual
stagnation state, and
isentropic stagnation
state of a fluid on an h-s
diagram.
16-2

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FIGURE 16-4
The properties of a
high-speed fluid
change significantly
during an adiabatic
stagnation process
(values from Example
16–1).
16-3

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FIGURE 16-5
16-4

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FIGURE 16-7
Propagation of a small pressure
wave along a duct.
16-5

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FIGURE 16-8
Control volume
moving with the small
pressure wave along a
duct.
16-6

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FIGURE 16-9
The velocity of
sound changes with
temperature.
16-7

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FIGURE 16-10
The Mach number can be
different at different
temperatures even if the
velocity is the same.
16-8

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FIGURE 16-14
The cross section of a
nozzle at the smallest
flow area is called the
throat.
16-9

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FIGURE 16-15
Derivation of the
differential form of the
energy equation for steady
isentropic flow.
16-10

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FIGURE 16-16
We cannot obtain
supersonic velocities
by attaching a
converging section
to a converging
nozzle. Doing so will
only move the sonic
cross section farther
downstream.
16-11

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FIGURE 16-17
Variation of flow
properties in subsonic
and supersonic nozzles
and diffusers.
16-12

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FIGURE 16-18
When Mt = 1, the
properties at
the nozzle throat
become the
critical properties.
16-13

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FIGURE 16-20
The effect of back
pressure on the
pressure distribution
along a converging
nozzle.
16-14

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FIGURE 16-21
The effect of back
pressure Pb on the
mass flow rate m and
the exit pressure Pe
of a converging
nozzle.
16-15

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FIGURE 16-22
The variation of
the mass flow
rate through a
nozzle with inlet
stagnation
properties.
16-16

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FIGURE 16-26
The effects of
back pressure on
the flow through
a converging–
diverging nozzle.
16-17

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FIGURE 16-28
Control volume
for flow across a
shock wave.
16-18

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FIGURE 16-29
The h-s diagram
for flow across a
normal shock.
16-19

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FIGURE 16-31
Entropy change
across the
normal shock.
16-20

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FIGURE 16-33
Isentropic and
actual
(irreversible)
flow in a nozzle
between the same
inlet state and
the exit pressure.
16-21

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FIGURE 16-35
Schematic and h-s
diagram for the
definition of the
diffuser efficiency.
16-22

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FIGURE 16-37
The h-s diagram
for the isentropic
expansion of
steam in a nozzle.
16-23