The Flow Research Unit has a proud experimentalist tradition, evident in the many
facilities developed over the years for research in steady and unsteady flows across
a wide range of Mach numbers.
Much of the design and manufacture of these facilities is done in house, and has
been possible because of the excellent standard of the School s workshop.
LOW SPEED WINDTUNNELS
- 1.5m x 1.5m Test Section
- Speed Range: 0 - 20 m/s
Last used for a study of full scale chimney and
- 900mm x 600mm Elliptical Cross Section
- Speed Range: 0 -80 m/s
Currently being used to perform a complete
aerodynamic analysis of a microlight aircraft design.
F4 Phantom II - model used to
demonstrate static stability
- 100mm x 100mm Cross Section
- Mach 1.4 - 3.6
Currently being used to investigate shock wave
interactions in non-planar aircraft engine inlets.
Schlieren images of
different inlet geometries
- 50mm x 50m Cross Section
- Mach 4, 5 and 6
Last used to investigate shock wave reflection.
15 wedges at Mach 5
Automated Shock Tube
- 180mm x 100mm Test Section
- Mach 1.1 - 2.0 normal shocks
Currently being used to investigate supersonic bow
shock reflections in valleys.
Tubes can be developed as needed.
Schlieren image of shock propagation
through a rectangular valley
BIFURCATED SHOCK TUBE
Bifurcated Shock Tube
- 160mm diameter Test Section
- Mach 1.4 - 1.6
Currently being used for examination of shock
diffraction and shock vortex interactions.
Holographic interferometry image
of shock-vortex interaction
LIQUID SHOCK TUBE
Vertical Liquid Shock Tube
- 56mm inner pipe diameter
- Gas-accelerated piston induces liquid shock
Last used in the forming of metal tubes and plates.
Extensions into the study of detailed metal figuring
Deformed metal samples
- 500mm x 500mm useful area
The water table is a useful tool for examining 2D
supersonic flows. Currently being used to investigate
2D shock interactions around various bodies.
Images of wave interaction
using water table
Drop Weight Tester
- Dual carriage system - pneumatic activation
- 4m max. drop height
Currently begin used to study liquid orifice discharge
coefficients under transient high-pressure conditions.
COMPUTATIONAL FLUID DYNAMICS (CFD)
An efficient in-house moving boundary Euler code
was developed and used extensively to study
We are also a user of the FLUENT CFD package.
We have considerable experience in validation of
CFD results for ourselves and in association with
research institutions in the US, Europe and Japan.
Shock interaction of passing
- Lasers - Pulsed Ruby and Argon s
- 1000 frames per second high-speed camera
- 1 million fps high-speed camera
(10 images superimposed)
- High-speed pressure transducers, digital
Images using shadowgraph, schlieren, holographic
interferometry and LVS (Laser Vapour Screen)
Slice of shock field using
Laser Vapour Screen