Department of Mechanical Engineering, Unit Catalogue 2008/09
| Credits: 6 |
| Semester: 1|
|Assessment: EX 100%|
|Before taking this unit you must take ME20022|
Aims: To improve the students' understanding of fundamentals of inviscid and viscous flow, principles of lift and drag, turbulence and compressibility.
After taking this unit the student should be able to:
* Estimate lift for an arbitrary aerofoil cross-sections.
* Calculate the load distributions over an arbitrary three-dimensional wing.
* Apply the boundary layer equations to laminar and turbulent flow.
* Estimate the drag, and predict lift and drag at high Mach numbers.
Problem solving and numeracy (taught and assessed).
Incompressible flow over aerofoils: irrotational flow over a circular cylinder, Kutta-Joukowski theorem, thin aerofoil theory, cambered and flapped aerofoil, vortex panel method, high-lift devices.
Incompressible flow over finite wings: induced drag, lifting-line theory, general lift distribution, lifting-surface theory, delta wings.
Fundamentals of viscous flow: viscosity and stress, fluid acceleration, conservation of mass and momentum.
Boundary layers: boundary layer equations, zero pressure gradient, separation, similarity solutions, arbitrary pressure gradient, boundary layer control in laminar flow, other thin shear flows.
Flow instabilities, transition and turbulence: stability theory, instability over a flat plate, factors affecting instability and transition, turbulent transport of momentum, turbulent boundary layer over a flat plate, turbulent drag reduction and separation control, turbulence measurement.
Lift and drag at high Mach numbers: Mach number regimes, normal and oblique shock waves, expansion waves, shock-expansion theory for supersonic aerofoils, subsonic and transonic flow over aerofoils, linearised supersonic flow, wings and influence of sweepback. Topics for self study that could be examined.