Fundamentals of Aerodynamics
B - Fundamental Principles and
Governing Equations
Wallace Leung
1
Acknowledgement is made on the materials
taken from John Andersons textbook,
Fundamentals of Aerodynamics, 5th ed., 2011,
McGraw-Hill.
9/11/2014
2
3
Review of
Fundamentals of Aerodynamics
G- Compressible flow through
nozzles, diffusers, and wind tunnels
Wallace Leung
Nov 2, 2014
11/3/2014
1
Acknowledgement is made on the materials
taken from John Andersons textbook,
Fundamentals of Aerodynamics, 5th ed., 2011,
Fundamentals to Aerodynamics A - Introduction to Aerodynamics
(Student Notes)
Wallace Leung
9/11/2014
1
Acknowledgement is made on the materials
taken from John Andersons textbook,
Fundamentals of Aerodynamics, 5th ed., 2011,
McGraw-Hill.
9/11/2014
2
Cont
Fundamentals to Aerodynamics C - Inviscid, Incompressible Flow
(Student Notes)
Wallace Leung
Aug 1 2014
Acknowledgements:
Materials in the slides are taken from the
textbook entitled Foundation in Aerodynamics
by Anderson.
2
Wright Brothers Biplane, 1903
Fundamentals of Aerodynamics
F (part 2) Sound and Shock Waves
Oct 29, 2014
Wallace Leung
1
Acknowledgement is made on the materials
taken from John Andersons textbook,
Fundamentals of Aerodynamics, 5th ed., 2011,
McGraw-Hill.
2
Contents
Speed of sound
S
Fundamentals to Aerodynamics D - Incompressible Flow over Airfoils
Wallace Leung
Aug 1, 2014
9/29/2014
1
Acknowledgements:
Materials in the slides are taken from the
textbook entitled Foundation in Aerodynamics
by John Anderson.
2
Scope
9/29/2014
3
Airfo
Fundamentals of Aerodynamics
E - Inviscid, Incompressible Flow
over Finite Wing
Wallace Leung
Acknowledgement is made on the materials
taken from John Andersons textbook,
Fundamentals of Aerodynamics, 5th ed., 2011,
McGraw-Hill.
10/16/2014
2
Beechcraft Ba
Fundamentals of Aerodynamics
F (Part I) - Preliminary Aspects of
Compressible Flow
Ver. 2 Oct 28, 14
Wallace Leung
Acknowledgement is made on the materials
taken from John Andersons textbook,
Fundamentals of Aerodynamics, 5th ed., 2011,
McGraw-Hill.
10/28
11/13/14
Prof. Leung
37001 Notes on workshop we had this afternoon for which we consider 3 cases.
Consider 3 cases:
Case 1:
M < 1 upstream of throat
M < 1 at throat
M < 1 downstream of throat
Select M < 1 at throat, say M = 0.5
@ d 2 = d t = 5.2mm, M t =
3.10 Prove that the velocity potential and the stream function for a uniform
ow, Equations (3.53) and (3.55), respectively, satisfy Laplaces equation.
3.10
¢=\/ocx; : [30;
ék 5y
a: z . 22: z 0
03 5Y2
Hence, Laplaces equation:
2 ' 2
~02? + i? = O + O =
ME 5"? o o /
Homework (Due Sept. 18, 2014)
° J. Anderson, Chapter 2
° Problems 2.2, 2.3, 2.5, 2.9 and 2.12. 2.2 Consider an airfoil in a wind tunnel (Le, a wing that spans the entire test
section). Prove that the lift per unit Span can be obtained from th