ASE 362K
Homework#1
Spring 2015
(due Feb 6)
Note: By design, there is no shaft or other power transfer in inlets or nozzles. Compressors and
turbines do have shaft power transfers. For air assume R = 287 J/kg-K, = 1.40.
1.
Air flows into a subsonic aircra

Homework #6
ASE 362K
Spring 2015
(due April 3)
1. Air at M1 = 2.6, p1 = 30 kPa and T1 = 298 K encounters an expansion of 30, as shown in the
sketch below (not to scale). The air-stream is then turned back to its original direction.
(a) Calculate M2 and M3

What is a sound wave?
Note: In a longitudinal wave, particles in the medium vibrate in the
same direction as the direction of wave propagation.
Notes on the speed of sound
In class, we defined the speed of sound as the speed at which a weak
(isentropic) d

ASE 362K
Spring 2015
General Solution Method for Moving/Reflected Shocks
Consider a moving or reflected shock, viewed in the shock-fixed reference frame. In this reference frame,
the shock is stationary, and the gas appears to be moving with pre-shock and

64 MODERN COMPRESIBHE FLOW: WITH HISTORICAL PERSPECTIVE
3.7 HUGONIOT EQUATION
The results obtained in Sec. 3.6 for the normal shock wave were couched in
terms of velocities and Mach numbers—quantities which quite properly empha-
size the fluid dynamic nat

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ON E-DIMENSIONAL FLOW 67
3.8 ONE-DIMENSIONAL FLOW WITH HEAT ADDITION
Consider again Fig. 3.5, which illustrates a control volume for one—dimensional
flow. Inside this control volume some action is occurring which causes the ﬂow
properties in region 2 to b

72 MODERN (‘OMPRESSIBIJE FLOW: WITH HISTORICAL PERSPECTIVE
subsonic ﬂow. If the ﬂow in region 1 of Fig. 3.5 is supersonic and corresponds to
point I in Fig. 3.11, then heat addition will cause conditions in region 2 to move
closer to point a, with a conse

CHAPTER
SEVEN
UNSTEADY WAVE MOTION
A wave of sudden rarcfaction. though mathematically possible. is an
unstable condition of motion; any deviation from absolute
suddenness tending to make the disturbance become more and
more gradual. Hence the only wave o

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Courtesy of Dr. Kiehne
Language of Thermodynamics
Matching Exercise
Match the descriptive phrases on the right with the appropriate terms on the left by placing the
phrase number in the blank adjacent to the term.
6
closed system
10
medium
4
1. No change

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ASE 362K
Spring 2015
Reynolds Transport Theorem
Before we derive the Reynolds Transport Theorem, recall the concept of a system - a macroscopic region
of interest separated from its surroundings by a boundary. A control mass (a closed system) can only
exc

ASE 362 K
Compressible Flow
Parvathy Prem
NASA
What Are Compressible Flows?
Engineering problems of the 18th, 19th and early 20th centuries
largely involved liquid flows and low speed gas flows. These are
incompressible flows (i.e. fluid density can be as

Transonic Drag
Reduction
Techniques
ASE 362 K
Spring 2015
The Swept Wing - 1
F-111
variable-sweep
Delays onset of drag divergence.
The Swept Wing - 2
Explanation 1:
A swept wing sees the component of velocity normal to the wing.
Mcr = 0.7
Mcr = 0.808
The

Wave Reflections from Free Boundaries
What happens outside the nozzle; specifically, how does the
jet interact with its surroundings?
Over-Expanded
Ideally Expanded
Under-Expanded
Slides courtesy Dr. Kiehne
Wave Reflections from Free Boundaries
What happe

QUASI-ONE—DIMENSIONAL FLOW 143
art than a science. Diffuser efﬁciency is inﬂuenced by a myriad of parameters
such as Au/A“, Me, entrance angle, second throat length, etc. Therefore, the
design of a diffuser for a given application must be based on empiric

Homework #5
ASE 362K
Spring 2015
(due March 13)
1.
Air flowing adiabatically through a circular duct has an inlet Mach number of 0.5 and an
inlet static pressure and temperature of 200 kPa and 280 K respectively. The duct is 20 m
long, 0.3 m in diameter,

ASE 362K (Compressible Flow) - Spring 2015
Review Checklist
Thermodynamics and Basic Principles:
Things you should know:
What it means for a flow to be compressible;
The ideal gas equation, and when it can be used;
How to determine specific gas constant f

THE UNIVERSITY OF TEXAS AT AUSTIN
Department of Aerospace Engineering & Engineering Mechanics
ASE 362K Compressible Flow
Spring 2015
SYLLABUS (updated 26th January 2015)
Unique No:
Instructor:
Time:
Location:
TAs:
Text:
Web page:
13250
Prof. Philip L. Var

ASE362K
Spring 2015
Compressible Flow - Practice Problems
1.
A supersonic stream at M1 = 3.6 flows past a compression corner with a deflection angle
of 20o. The resulting shock wave is reflected from a wall which is parallel to the upstream
supersonic flo