Mais conteúdo relacionado Mais de Mete Cantekin (9) Cengel ch161. CHAPTER
16
Thermodynamics of
High-Speed Gas Flow
2. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-1
Steady flow of a fluid
through an adiabatic
duct.
16-1
3. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-3
The actual state, actual
stagnation state, and
isentropic stagnation
state of a fluid on an h-s
diagram.
16-2
4. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-4
The properties of a
high-speed fluid
change significantly
during an adiabatic
stagnation process
(values from Example
16–1).
16-3
5. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-5
16-4
6. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-7
Propagation of a small pressure
wave along a duct.
16-5
7. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-8
Control volume
moving with the small
pressure wave along a
duct.
16-6
8. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-9
The velocity of
sound changes with
temperature.
16-7
9. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-10
The Mach number can be
different at different
temperatures even if the
velocity is the same.
16-8
10. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-14
The cross section of a
nozzle at the smallest
flow area is called the
throat.
16-9
11. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-15
Derivation of the
differential form of the
energy equation for steady
isentropic flow.
16-10
12. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
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
13. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-17
Variation of flow
properties in subsonic
and supersonic nozzles
and diffusers.
16-12
14. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-18
When Mt = 1, the
properties at
the nozzle throat
become the
critical properties.
16-13
15. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-20
The effect of back
pressure on the
pressure distribution
along a converging
nozzle.
16-14
16. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
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
17. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-22
The variation of
the mass flow
rate through a
nozzle with inlet
stagnation
properties.
16-16
18. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-26
The effects of
back pressure on
the flow through
a converging–
diverging nozzle.
16-17
19. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-28
Control volume
for flow across a
shock wave.
16-18
20. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-29
The h-s diagram
for flow across a
normal shock.
16-19
21. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-31
Entropy change
across the
normal shock.
16-20
22. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-33
Isentropic and
actual
(irreversible)
flow in a nozzle
between the same
inlet state and
the exit pressure.
16-21
23. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-35
Schematic and h-s
diagram for the
definition of the
diffuser efficiency.
16-22
24. Copyright © The McGraw-Hill Companies, Inc. Permission required for reproduction or display.
FIGURE 16-37
The h-s diagram
for the isentropic
expansion of
steam in a nozzle.
16-23