THEORY OF
WING SECTIONS
Including a Summary of Airfoil Data
By IRA H. ABBOTT
DIRECTOR OF AERONAUTICAL AND SPACE RESEARCH
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
and ALBERT E. VON DOENHOFF
RESEARCH ENGINEER. NASA
DOVER PUBLICATIONS, INC.
NEW YORK
Cop
Particle Image Velocimeter
Adapted from various websites and
AAE 334L/ AAE 520
slides at Purdue University
Why use imaging?
Conventional methods
(HWA, LDV)
Single-point measurement
Traversing of flow domain
Time consuming
Only turbulence statistics
z
A
AE 314/315 Notes
Spring 2015
The material has been lifted, adapted and inspired from various sources[1, 2, 7, 5, 6, 4, 3] which
are listed at the end of this document
1
Pressure measurements
Pressure is one of the most important and common measurements ma
AE 314/315 Notes
Spring 2015
The material has been lifted, adapted and inspired from various sources[1, 2, 7, 5, 6, 4, 3] which
are listed at the end of this document
1
Circulation theory of lift
The ow over a wing of an airplane is a very complicated ow
AE 314/315 Notes
Spring 2015
The material has been lifted, adapted and inspired from various sources[1, 2, 7, 5, 6, 4, 3] which
are listed at the end of this document
1
1.1
Coecient of pressure (Cp)
Denition
The coecient of pressure at a point is dened as
AE 314/315 Notes
Spring 2015
The material has been lifted, adapted and inspired from various sources[1, 2, 7, 5, 6, 4, 3] which
are listed at the end of this document
1
Two-dimensional drag
1.1
Denition
Drag over an object can be considered as an aerodyna
AE 314 Notes
Fall 2015
The material has been lifted, adapted and inspired from various sources[1, 2, 7, 5, 6, 4, 3] which
are listed at the end of this document
1
1.1
Three-dimensional airfoils or wings
Induced Drag
The ow over an airfoil is a two dimensi
Hot-Wire Anemometry
Purpose:
to measure mean and fluctuating velocities in
fluid flows
http:/www.dantecmt.com/
www.tsi.com/
Adapted from manufacturers websites and AAE 334L/ AAE 520
slides at Purdue University
Principles of operation
Consider a thin wire
AE 314/315 Notes
Spring 2015
The material has been lifted, adapted and inspired from various sources[1, 2, 7, 5, 6, 4, 3] which
are listed at the end of this document
1
Boundary layers
When a body, such as an airfoil, is in motion within a uid at rest the
AE 301 Aerodynamics I Spring 2015
Solutions to Problem Set 6
1. (5 pts) Show how to nd the velocity potential for a lifting circular cylinder in a uniform
ow of velocity V with circulation . Find the velocity components in this ow eld
and on the surface o
AE 301 Aerodynamics I Spring 2015
Answers to Problem Set 2
1. (5 pts) Write a short MATLAB code (or use another language if you prefer) to calculate and plot the pressure, density, temperature and viscosity (in both SI and English/American units) in the I
AE 301 Aerodynamics I Spring 2015
Solutions to Problem Set 7
1. (5 pts) For a at plate airfoil, use the thin airfoil theory to plot the form of the
distributions of chordwise dierential pressure coecient. Choose three values of angle
of attack to illustra
AE 301 Aerodynamics I Spring 2015
Answers to Problem Set 4
1. A static thrust stand is being designed for testing a jet engine in the lab. The following
conditions are expected for a typical test: intake air velocity = 250 m/s, exhaust gas
velocity = 600
AE 301 Aerodynamics I Spring 2015
Answers to Problem Set 5
1. (5 pts) Starting from the momentum equations for an inviscid uid with no body forces
(i.e., the Euler equations), prove that Bernoullis equation will hold between any two
points in an irrotatio
AE 301 Aerodynamics I Spring 2015
Answers to Problem Set 3
1. (5 pts) Show (separately) how the integral and differential forms of the continuity equation
can be simplied for application to uid problems involving: (a) steady ow, (b) steady,
incompressible
AE 301 Aerodynamics I Spring 2015
Answers for Problem Set 1
1. (5 pts) For a given point on the wing of a large commercial airplane during ight the pressure
and temperature of the air are measured to be 1.8 104 N m2 and 70.15 C, respectively.
Calculate th
AE 301 Aerodynamics I
Practice Mid-Term Exam 2
Total of 60 points
Name.
IMPORTANT: This examination is closed book. You are allowed
a single handwritten formula sheet; this sheet must be handed in
with your answers. Time allowed: 1 hour.
Answer all questi
AE 301 Aerodynamics I
Practice Mid-Term Exam 1
Total of 60 points
Name.
IMPORTANT: This examination is closed book. You are allowed
a single handwritten formula sheet; this sheet must be handed in
with your answers. Time allowed: 1 hour.
Answer all questi
Rocket Vehicle Dynamics
Types of rocket engines
There are two categories of rockets, high thrust rockets and low thrust
rockets. High thrust rockets have an acceleration + 1, i.e. an
acceleration much greater than the acceleration of gravity on the surfac
Gauss Problem of Orbit Determination
Approximate Solution of the Two-Body Problem
by Taylor Series Expansion
We show that the radius vector r> can be expressed as a linear
combination of the initial radius vector and initial velocity vector. The
coefficie
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Orbit Determination from Initial Conditions
The problem of two bodies was formulated in terms of a second order
differential equation governing the relative motion r>
. # r.>#
.r<$
with the initial conditions
r>! r! and v>! . r.>! v!
Since the position v
The Position of a Body in Orbit at a Given Time
For the two-body problem, we developed an expression for the equation
of the orbit in polar coordinates:
< +"
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On the one hand, this is a very important result, since it tells us that all
the orb
AE 313 SPACE MECHANICS
CLASS NOTES
Yechiel J. Crispin
Department of Aerospace Engineering
Embry-Riddle University
Daytona Beach, FL 32114
e-mail: crispinj@erau.edu
The Two-body Problem
The gravitational two-body problem is an initial value problem. It can
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