Ch7 Compressible Flow
Introduction: TYPES OF FLOW
1. Continuum vs Free Molecular Flow:
3. Incompressible vs Compressible Flow:
Knundsen No. Kn= meanfree path / Characteristic length L
Mach No. M = Velocity U / Sound Speed a
2. System (Lagragian) vs Contro
Introduction
The first practical supersonic wind tunnel, built by
A. Busemann in Germany in the mid-1930s.
A large hypersonic wind tunnel at the U.S. Air Force
Wright Aeronautical Laboratory, Dayton, Ohio.
Compressible Channel Flow
Quasi-1-D Flow
A quasi-
2016/4/19
Ch9 Oblique Shock Wave
Introduction
oblique
shock
waves
Expansion
waves
M=1.7
1
2016/4/19
Supersonic flow over a corner
Mach Waves
Small disturbances created by a slender body (<1) in a supersonic flow will
propagate diagonally away as Mach wave
Ch8 Normal Shock Wave
Occurance of Normal Shock Waves
A normal shock wave appears in many types of supersonic
flows. Two examples are shown in the figure. Any bluntnosed body in a supersonic flow will develop a curved bow
shock, which is normal to the flo
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1
2016/5/31
2
2016/5/31
According to Eqs. (12.1) to (12.8), all disturbances created at the wall
(represented by the perturbation potential ) propagate unchanged away from
the wall along Mach waves.
3
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Note that is positive when measur
Chapter 5: Incompressible Flow over
Finite Wings
5.1 Introduction
finite wings, downwash, induced drag
5.2 Vortex Theory
principle: the vortex filament
Biot-Savart law
Helmholtzs vortex theorems
5.3 The Classical Lifting-Line Theory
elliptical and general
APPLIED AERODYNAMICS
Aerodynamics is an applied science to learn:
External flow: the prediction of forces and moments on, and heat
transfer to, bodies moving through a fluid.
- Lift, drag and moments on flying objects (insects, birds, airplanes, missiles
2016/8/23
OUTLINE FOR Chapter 2
Incompressebile Form of
the Continuity & Navier-Stokes
Equations in Cartisian Coordinates
u v w
V
0
x y z
REVIEW OF VECTOR RELATIONS (I)
AERODYNAMICS (W1-2-2)
1
2016/8/23
REVIEW OF VECTOR RELATIONS (II)
Scalar Fields (p
2015/12/4
OUTLINE FOR Chapter 4
AIRFOIL NOMENCLATURE
The leading edge circle: (usually radius = 0.02 chord length c)
The trailing edge:
The chord line: Straight line connecting the center of leading edge circle and the trailing edges.
The leading edge:
Th
2013/6/3
HIGH LIFT DEVICES
When an aircraft is landing or taking off, specially high
values of lift coefficient are required in order to maintain
flight at the desired low speeds.
L
1
V 2 SC L
2
Increasing the area S.
Increasing the lift coefficient C
AERODYNAMICS(I)
Instructor: Prof. T.S. Leu ()
Department of Aeronautics and Astronautics
Email: tsleu@mail.ncku.edu.tw
Lecture hours: Tue 09:10 ~10:00/ Fri 10:10 ~12:00
I)
Course goals
II) Textbook & Reference
III) Course outline
IV) Homework and term pro
5th Jan., 2016
Quiz # 9 of the course Mechanisms I of ME, NCKU
91802
62159-45
1. Fig. 1 shows a truck with a lifting mechanism. Neglect the weight of the other links.
(a) List all two-force members [2%]
(b) List all three-force members [2%]
(c) Show the l
91802
Dec.4,2012
62159-45
1. [14%] It is given that r1 = 5 cm,r3 = 5 cm, and r4 = 3.5 cm for a four-bar mechanism. Link 2 is driven at
a constant rate in the counterclockwise direction.
(a) Determine the range of values of r2 so that the transmission ang
101 30th Oct., 2012
91809
62249
1.
[10 %] For the mechanism as shown in Fig. 1-1, please (a) give its skeleton drawing, and complete
labeling each link and each joint, (b) determine the mobility, with specifying number of links, the type
of each joint, an
103 13th Jan., 2015
91809 62249
1. For the mechanism as shown in Fig. 1, H and G are the centers of curvature of links 4 and 5, respectively,
corresponding to location D, and F is that of link 3 corresponding to C, if slider 2 moves with a velocity
of 20
102
Oct. 29, 2013
91809
62249
1. [10%] For the mechanism as shown in Fig. 1, please (a) complete the skeleton drawing with complete
labeling, (b) determine the mobility, with specifying number of links, the type of each joint, and count
the number of eac
104
27th Oct., 2015
91807
62251
1. Figure 1 shows a front-end loader mechanism.
(a) Draw its skeleton diagram. [5%]
(b) Label each link and each kinematic pair (joint) with a notation in the skeleton diagram. Specify the
type of each joint. [5%]
(c) Deter
91802 62159-45
1.
Dec. 9, 2014
[20%] For the quick-return mechanism shown, link 2 rotates counterclockwise. We know that
r1 = 5 cm, r2 = 3 cm, r4 = 10 cm, r5 = 2 cm, and r6 = 9 cm. Analytically determine the
followings.
(a) the time ratio of the motions
91805
62231-17
1. A slider crank mechanism is shown in the figure. The offset is 1.0 cm, the length
of link 3 is 3.5 cm. Link 2 is the input link, which rotates with a constant angular
velocity in CCW direction. Please check the transmission angle of thi
104
91805
8th Dec., 2015
62231-17
1. An arbitrary position of a six-link mechanism is shown below. Link 2 is the input, which rotates at a
constant angular velocity 2. The lengths of O1 O2 (r1) is 10 cm. The lengths of link 2 (r2) is 5 cm. Link 6
is the
91809
62249
1. For the mechanism as shown in Fig. 1, please (a) complete the skeleton drawing with complete
labeling, (b) determine the mobility, with specifying number of links, the type of each joint, and
count the number of each type of joints. [10]
(
Jan. 12, 2016
91802 62159-45
1. [30] For the following mechanism, it is given that r2 = 3 cm, r3 = 6 cm, r4 = 5 cm, AB = 2 cm, BC = 2 cm, and O5C = 6.1 cm. Link 2 rotates
counterclockwise with a constant angular velocity of 10 rad/sec. (a) Draw the velo
CHAPTER
2
LabVIEW Graphical Programming
Environment
LabVIEW constitutes a graphical programming environment that allows one to
design and analyze a DSP system in a shorter time as compared to text-based
programming environments. LabVIEW graphical programs
Chapter 6
Using Entropy
Clausius Inequality
Considering a system receives energy Q at its boundary at temperature T from a
thermal reservoir at Tres and develops work W . By introducing an intermediary
reversible cycle which receiving Q from the reservoir
5892 Training
MATLABSFunctionfor
DynamicSystemSimulation
8Jun16
1
by Dr. Chao-Chung Peng
Simulink SFunction
5892 Training
WherecanwegetthemfileofSfuntion?
C:\ProgramFiles\MATLAB\R2009b\toolbox\simulink\blocks
sfuntmpl.m
function [sys,x0,str,ts,simStateCom