2002/03 MODULE SPECIFICATION Module Code: AERO316
Faculty of Engineering, University of Liverpool
DEPARTMENT OF ENGINEERING: Aerospace Engineering
Module title:
CATS level: 3 CATS value: 15 credits Semester: 1st
Staff (with email addresses)
Co-ordinator: Dr D Nicolaou
(Nicolaou@liv.ac.uk)
Moderator:
Lecturer(s):
Study hours
Dr D Nicolaou / Dr A Millward
Lectures:
Other:
36 Seminars/tutorials:
Pre-requisites: Co-requisites:
Dr A Millward
(a.millward@liv.ac.uk)
Labs:
Private study:
0
72
Optional:
-
Modules for which this module is a pre-requisite:
- AERO213 None
Availability to (student groups/years):
Compulsory/core:
Aero3 BEng/MEng
Learning and Teaching Strategies (eg, traditional lectures, supervised design classes)
Traditional lectures
Module Description
Lecture/
Lab no.
Content
Incompressible Aerodynamics
Introduction: Differences between viscous and inviscid flow; generation of lift and drag.
Introduction to the Navier-Stokes equations, conservation of mass and continuity.
Description of flow around aerofoils. Definition of centre of pressure; calculation of the lift and drag coefficients from a pressure distribution. Aerodynamic Centre. Introduction to drag force: skin friction, form and induced drag.
Potential Flow: Description of potential flow. Introduction to Laplace’s equation. Definition of streamfunction and velocity potential. Derivation of equations for the streamfunction and velocity potential for a source, sink, vortex, doublet and source-sink pair. Combinations of basic flows. Complex variables. Potential flow around a circular cylinder. Circulation and lift.
Conformal Transformation Techniques: Introduction to transformation methods. The
Zhukovsky transformation. Conformal transformation of a circle to a flat plate, ellipse or aerofoil geometry. Calculation of lift; the Kutta condition. Limitations of conformal transformation methods.
Thin Aerofoil Theory: Notation. Approximations and assumptions. Derivation of the relevant equations. Calculation of the lift and pitching moment coefficients. Flat plate aerofoil example. General solution for any camber shape. Thickness problem, calculation of the pressure distribution.
Finite Wing Theory: Notation. Fundamentals of line vortices. Biot-Savart law, calculation of induced velocities from finite and semi-infinite vortices. Horseshoe vortex approximation. Description of ground effect. Lifting line theory and applications.
Prandtl’s integral equation. Calculation of lift and pitching moment coefficients.
Introduction to flow over swept wings.
Compressible Aerodynamics
Quasi One-Dimensional Inviscid Flow: Brief revision of the governing equations, as developed in the second year fluid mechanics, is given together with the normal shock wave relations.
(continues)
Page 1 of 3

2002/03 MODULE SPECIFICATION Module Code: AERO316
Oblique Shock Waves and Expansion Waves: Oblique shock wave relations. Supersonic flow over a wedge. Detached shock wave ahead of a blunt body in supersonic flow.
Reflection of shock wave at surface. Interaction of shock waves. Prandtl expansion wave.
Use of shock expansion theory to determine aerodynamic loads on two-dimensional wings.
Definition of wave drag. Brief introduction to the differences between subsonic, transonic and supersonic flow past wings.
Linearised Flow: Development of linearised equations for two-dimensional flow.
Calculation of flow over aerofoils, the Prandtl-Glauert rule and the critical Mach number.
Application to supersonic flow.
One-Dimensional Flow: Flows with friction i.e. Fanno Flow. Flow with heat transfer i.e.
Rayleigh Flow. Applications to flows with combustion and flows in long pipelines with friction present.
Learning Outcomes
Knowledge and Understanding:
On successful completion of the module, students should be able to demonstrate knowledge and understanding of:
 the limitations of inviscid flow theory
 the relationship between pressure distributions and aerodynamic forces acting on a body



Potential flow theory, streamlines
Conformal transformation and its general uses in aerodynamics
Thin aerofoil theory

Finite wing theory
 the physics of trailing edge vortices and their effects on aircraft aerodynamics
 the changes in pressure and temperature through normal and oblique shock waves
 shock-expansion theory and its application to two-dimensional wings
 the role of linearised flow in the design of two-dimensional aerofoil sections
 flows in ducting systems in which compressibility is important and friction and heat transfer at the duct walls are present
Intellectual Abilities:
On successful completion of the module, students should be able to demonstrate ability in applying knowledge of the above topics by providing descriptions and explanations and by carrying out analysis and calculations:
 aerodynamic (inviscid) forces and moments acting on 2D and 3D wings using linear theories.
 pressure and temperature rises through normal and oblique shock waves, and use of shockexpansion theory to calculate loads on two-dimensional wings.
 pressure losses and flow rates in ducting systems in which compressibility is important and friction and heat transfer at the duct walls are present.
Practical Skills
On completion of the module, students should be able to show experience and enhancement of the following discipline-specific practical skills:
 application of mathematical and analytical techniques to estimate aerodynamic characteristics of subsonic and supersonic flows
General Transferable Skills
On completion of the module, students should be able to show experience and enhancement of the following key skills:

Mathematical and analytical skills
Page 2 of 3

2002/03
Assessment
Formal exam:
MODULE SPECIFICATION
Weighting % Timing
100 January
Module Code: AERO316
Duration/other comments
3 hours
September Resit opportunity: No
Recommended reading:
1.
Houghton, EL and Carpenter, PW, Aerodynamics for Engineering Students, Edward Arnold, 4 th
Edition, 1993.
2.
Anderson, JD, Fundamentals of Aerodynamics, 2 nd Edition, McGraw-Hill, 1991.
3.
Anderson, JD, Modern Compressible Flow, McGraw Hill International Editions.
External Examiner responsible for module:
Aerospace Engineering
Version date: 12 October 2002
Page 3 of 3