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 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

EMBRY-RIDDLE AERONAUTICAL UNIVERSITY
Daytona Beach Campus
AE 413: Aircraft Stability and Control
Instructor: Dr. Claudia Moreno
Fall 2015
HOMEWORK #4
Due Date: October 28, 2015
1. (15 points) Derive the yawing moment caused by the left wing dihedral angle

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 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

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 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

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 314/315 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
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
Pressure measurements
Pressure is one of the most important and common measurements ma

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

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

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

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AE 301
Aerodynamics I
Fall 2015
Homework 6 (due 10/13/15)
1.
(15 points) Study the flow around a NACA 0010 airfoil at =0o and 5o using a panel code.
Plot the Cp distribution. Show the effect of the number of panels and record Cl, Cd and any
other useful q

AE 301
Aerodynamics I
Fall 2015
Homework 5 (due 10/1/15)
1. (2 points) It is desired to simulate flow past a two-dimensional ridge or bump by using a streamline
which passes above the flow over a cylinder with radius a. The bump is to be a/2 high, where a

HE 30/ #bmeWar/c Z 152” 20/§
ﬁlo/action?
1. (1 pts) Write a short MATLAB code (or use another language if you prefer) to cal—
culate and plot the pressure, density, temperature and viscosity (in both SI and En-
glish / American units) in the International

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AE 301
Aerodynamics I
Fall 2015
Homework 4 (due 9/24/15)
1. (3 points) You have landed on Mars as one of the members of the first expeditionary missions.
You land at the equator where, using a spherical coordinate system, your position is = /2, =
0, and r

AE 301
Aerodynamics I
Fall 2015
Homework 3 (due 9/17/15)
1. [3 points] A conical funnel of half angle drains through a small hole of diameter d at the
vertex. The speed of the liquid leaving the funnel is approximately V 2 gy , where y is the
height of th