Take-Home Midterm Examination
1.) Find the ow eld around a circular cylinder of radius R placed in a simple shear ow in a
perfect uid, i.e., assume that far from the cylinder the velocity eld has cartesian components
u = Ay, v = 0. Hints: Find the stream
Thin Wings in Compressible Flow
We now begin to investigate the eects of compressibility while still remaining in the realm of
inviscid ow. As in the incompressible case, we will consider thin airfoils in steady ow. With
variable density we have seen that
Lecture 3. Details on Vorticity and Helmholtzs Theorems
The uid vorticity is dened by =
u = curl(u ) where u = (u, v, w), is the uid velocity
vector, and = (/x, /y, /z ). (Sometimes it is more convenient to use u = (u1 , u2 , u3 ), and
= (/x1 , /x2 , /x3
Lecture 1. Fluid Kinematics
Description of Fluid Motion.
Before we look at the full 3D problem, lets consider the 1D case it contains all the basic ideas.
Consider a continuum that can move only in one direction, say x. At some initial time, say t = 0,
su
ENGR 685 Aerodynamics
Fall Term 2002
Course Information
Instructor: John E. Molyneux
Oce: Kirkbride 103
Telephone:610-499-4061
E-mail: John.E.Molyneux@widener.edu or jem@snip.net
Course Web Page: http:/www2.widener.edu/ jem0002, or via Widener home page b
Poissons Integral Formula and Some Consequences
Separation of Variables on a Disk of radius R
Let D = cfw_(r, ) : 0 r < R, < be the disk of radius R, and consider the problem of
solving Laplaces equation on D subject to Dirichlet conditions on D = cfw_(R
Note on the Panel Method
Background on the method
The panel method is a numerical approach to the solution of the potential problem
=
2 2
+
= 0, x = (x, y ) D
x2
y 2
and
= G, x D,
n
where D is a domain (the uid exterior to a body in our case) with bound
Brief Summary of Thermodynamics
We are going begin to consider compressibility and airfoils in compressible ow. Before embarking
on this study, we need to review some thermodynamic concepts. Probably the most authoritative
recent text on the subject, as i
Summary of Thin Airfoil Theory
I give a short overview of the basic equations of thin wing theory, with a list of those results which are
used in the Prandtl theory of nite wings. An excellent reference for this material is K. Karamcheti,
Principles of Id