The Boundary Layer Tunnel
The “Bob” Wind Tunnel
- Hypersonic wind tunnel with a run time of 7sec (Mach 4, 5 and 6) and 6” diameter circular test section
- Trisonic wind tunnel 0.15mx0.3m (Mach 0 to 0.8, 1.8).
- 1.2m x 0.3m x 5m open-circuit boundary layer tunnel, max speed 40m/s
- 0.9m x 0.9m x 5m open-circuit wind tunnel (“Bob”), max speed 25m/s, useful for “Environmental” wind turbine work.
- 1.2m x 0.9m x 2m open-circuit “Project” wind tunnel, max speed 50m/s, useful for Aerodynamics studies.
- 0.5m x 0.5m x 1m open-circuit wind tunnel, max speed 40m/s
- 0.5m x 0.5m x 2m closed-circuit water tunnel, max speed 2m/s
- 0.5m x 0.3m x 5m tilting flume, max speed 1m/s
Our measurement capabilities include:
- Force and moment measurement (overhead balance (Project tunnel), 6 component strain gauge balances
- Schlieren systems for visualisation of high speed flow
- Scalar field measurements (Planar laser-induced fluorescent)
- Full-surface temperature and pressure measurements (temperature-and pressure-sensitive paints)
- Temporally-resolved high-spatial resolution near-wall velocity measurements (one, two or three velocity-component hot-wire anemometry and laser Doppler anemometry)
- High-spatial resolution velocity measurements (2D and stereo Particle-Image Velocimetry)
Wave rider hypersonic flow experimental setup
- Bill Crowther, AFloNexT EU Funded project looking at fluidic trailing edge controls for civil transport aircraft, 2014-2017, £150k, facility used: the “Project” wind tunnel and transonic wind tunnel.
- S. Zhong, “Combined experimental and computational study of synthetic jets injected into separated turbulent boundary layers pertinent to high-lift aerodynamics”, sponsored by EPSRC & Airbus UK, 2007-2011, £310k, facility used: the Boundary Layer Tunnel.
- S Zhong, “An Experimental Study of Unsteady Wake-Induced Boundary Layer Transition in Turbomachinery”, sponsored by EPSRC, 2006-2010, £200k, facility used: 0.5mx0.5 closed-circuit water tunnel.