# MAE3401 - Aerodynamics 2 - 2019

## 6 points, SCA Band 2, 0.125 EFTSL

Refer to the specific census and withdrawal dates for the semester(s) in which this unit is offered.

Faculty

Engineering

Organisational Unit

Department of Mechanical and Aerospace Engineering

Chief examiner(s)

Coordinator(s)

Unit guides

Offered

Clayton

• First semester 2019 (On-campus)

Prerequisites

MAE2402, MAE2404 and 12 engineering credit points at level two

Co-requisites

None

Prohibitions

MEC3451

## Synopsis

This unit develops further the students' physical understanding and analytical skills by including compressibility effects and the viscous nature of aerodynamic flows and translates that into the ability to formulate, analyse and solve very general aerodynamic problems. It covers control volume analysis of steady, one-dimensional, linear and nonlinear compressible flows. Nozzle flows. Steady, supersonic, two-dimensional linear and nonlinear flows. Linearised compressible subsonic and supersonic flow. Introduction to transonic and hypersonic flow. Control volume analysis of viscous incompressible flow, boundary layer flow and free shear flows like jets and wakes, including momentum integral analysis, similarity analysis and similarity solutions of these equations as they pertain to wall bounded and free shear flows. Application of this knowledge to simple design problems.

## Outcomes

At the successful completion of this unit you will be able to:

1. Formulate the equations governing compressible airflow, normal and oblique shocks and expansion fans using control volume analysis and the fundamental thermodynamic properties of gases
2. Apply the quasi-1D approximation principle to design supersonic nozzles (e.g. rocket propulsion), wind tunnels and diffusers.
3. Determine lift and drag on supersonic aerofoils using non-linear methods or linearised approximations as appropriate.
4. Determine the governing equations for viscous boundary layer flows, and apply these equations to calculate the drag due to skin friction in laminar and turbulent boundary-layer flows.
5. Determine engineering solutions for the aerodynamics of flight vehicles by synthesis of incompressible, compressible, inviscid and viscous flow theories

## Assessment

Continuous assessment: 40%

Final Examination (3 hours): 60%

Students are required to achieve at least 45% in the total continuous assessment component and at least 45% in the final examination component and an overall mark of 50% to achieve a pass grade in the unit. Students failing to achieve this requirement will be given a maximum of 45% in the unit.