Course Title: Aerodynamics 2

Part B: Course Detail

Teaching Period: Term2 2011

Course Code: AERO5402

Course Title: Aerodynamics 2

School: 130T Engineering (TAFE)

Campus: City Campus

Program: C6011 - Advanced Diploma of Engineering (Aerospace)

Course Contact : Program Manager

Course Contact Phone: +61 3 9925 4468

Course Contact

Name and Contact Details of All Other Relevant Staff

Amir Zokaei Fard

Contact phone: 99254184

Contact Email:

Nominal Hours: 40

Regardless of the mode of delivery, represent a guide to the relative teaching time and student effort required to successfully achieve a particular competency/module. This may include not only scheduled classes or workplace visits but also the amount of effort required to undertake, evaluate and complete all assessment requirements, including any non-classroom activities.

Pre-requisites and Co-requisites

AERO5389 Aerodynamics 1

Course Description

The purpose of this course is to provide training in aerodynamics and stability analysis, problem solving, and high speed flight.

National Codes, Titles, Elements and Performance Criteria

National Element Code & Title:

VBH737 Aerodynamics 2

Learning Outcomes

1. Discuss and perform calculations relating to aircraft longitudinal static stability.
2. Discuss and perform aerodynamic calculations for manoeuvring flight.
3. Discuss and apply formulae for the calculation of aircraft range and endurance.
4. Describe the characteristics of supersonic airflow and perform related calculations.
5. Discuss transonic and supersonic airflow around aerofoils and perform related calculations.

Details of Learning Activities


A participant will be expected to be able to:
- Do calculations relating to aircraft stick-fixed and stick-free longitudinal static stability
- Discuss the relationship between stick-fixed and stick-free longitudinal static stability
- Describe the effect of the fuselage, the powerplant, engine nacelles and propeller slipstream on longitudinal static stability
- Define and calculate “ elevator hinge moment coefficient”
- Calculate the elevator angle necessary to maintain trimmed flight and discuss the effect of moving the aircraft center of gravity on aircraft stability and the elevator deflection angle
- Solve aircraft manoeuvre (steady level coordinated turn) problems
- Explain the relationship between load factor, stall speed, angle of bank, speed of turn and the radius of turn
- Calculate range and endurance for a typical piston engine and jet engine powered aircraft
- Describe “Specific Fuel Consumption” for piston engine (SFC) and jet engine (TSFC)
- Describe the conditions for maximum endurance and range for piston engine and jet engine aircraft
- Define terms such as speed of sound, Mach number, Mach line, Mach angle, normal shock, oblique shock, critical Mach number, shock attachment Mach number
- Define “isentropic” and “adiabatic” flow
- Do calculations using the oblique shock chart
- Describe the variation of CL, CD and total drag of an aerofoil across the transonic range
- Explain the movement of centre of pressure across the transonic range
- Describe the advantages and disadvantages of swept wings relative to high speed flight
- Describe the area rule for minimising transonic drag
- Explain why trim drag increases on a conventional aircraft in high speed flight
- Calculate CL and CD for simple supersonic aerofoil sections (Ackeret Linearised Theory)
- Describe leading edge characteristics for subsonic and supersonic aerofoil
- Describe common features of supersonic wings

Teaching Schedule


Week 1: Static Longitudinal Stability- Stick fixed
Week 2: Static Longitudinal Stability- Stick free
Week 3: Miscellaneous Effects on Static stability and Tail load calculation
Week 4: Calculation of aircraft range and endurance
Week 5: Aerodynamic calculation for manoeuvring flight
Week 6: Characteristics of supersonic airflow (overview)
Week 7: Calculations related to isentropic process
Week 8: Calculations related to normal and oblique shocks
Week 9: Calculations related to expansion wave and supersonic airflow inside subsonic and supersonic nozzles
Week 10: Revision
Week 11: Examination

Learning Resources

Prescribed Texts

No text book is prescribed for this course, however, other related resources such as study guides, problem sheets and formula sheets generated by the course lecturer and approved links to useful material on external web-sites will be provided on the RMIT Distributed Learning System (DLS).


  Irving, F.G. 1966, An Introduction to the longitudinal Static Stability of Low-Speed Aircraft, Pergamon Press, London
Anderson, J.D., 1989 Introduction to Flight, McGraw-Hill., ISBN 0070016410
Anderson, J.D., 2001, Fundamentals of Aerodynamics, 3rd Ed., McGraw-Hill, ISBN 0072373350
Anderson, J.D., 1999, Aircraft Performance & Design, McGraw-Hill, ISBN 0070019711
Pamadi, B. N., 2004, Performance, Stability, Dynamics, and Control of Airplanes, 2nd Ed., AIAA Education Series

Other Resources


Asselin, M., 1997, An Introduction to Aircraft Performance, EIAA Education Series, ISBN 156347221X
Bertin, J.J , 2002, Aerodynamics for Engineers, Prentice Hall, ISBN 0130646334
Bertin, J.J & Cummings, R.M., 2009, Aerodynamics for Engineers, Prentice Hall, ISBN-13 978-0-13-227268
Clancy, L.D., 1986, Aerodynamics, Longman Scientific and Technical, ISBN 0582988802
Eshelby, M.E., 2000, Aircraft Performance; Theory and Practice, AIAA Education Series
Haughton Carpenters, 1993, Aerodynamics for Engineering Students, 4th Edition, Edward Arnold., London
Kermode, A.C., 1996, Mechanics of Flight, Longman Press, ISBN 0582237408
Phillips, W. F., 2004, Mechanics of Flight, John Wiley & Sons, ISBN 0471334588
Shevell, R.S. 1989, Fundamentals of Flight, Prentice Hall, ISBN 0133390608

Overview of Assessment

To successfully complete this course the student is required to pass written assessment tasks and demonstrate skills and ability by completing pratical tasks to aerospace standard.

Assessment Tasks

You will be assessed in various ways to ensure you meet the requirements of the course. Your ability to explain the principles of various topics and apply the aerodynamic theory to of fixed wing aircraft will be tested through individual assignments and exam works. Successful graduation from the course is achieved when the student attains at least 50% of total mark AND his/her accumulation of exams marks is NOT less than 50% of total exams mark.

Assessment Matrix


Contribution of each task towards the final result is as follows:

Assignment 1: 12%   - To Be Submitted by 25th July 2011
Assignment 2: 18%  -  Part 1 to Be Submitted by 29th August 2011 and Part  2 to Be Submitted by 8th September 2011
Examination: 70%    - To be conducted on 10th October 2011

Course Overview: Access Course Overview