Experimental aerodynamics

The experimental aerodynamics group undertakes an extensive variety of carefully designed laboratory experiments using novel flow diagnostic and measurement techniques. The aim of our research is to understand the physics of complex flow phenomena and to generate aerodynamic data for the development of advanced aerodynamic design concepts and flow models. 

 

Why don't you come and join us?

Our PhD projects available

The Boundary layer Tunnel
The Boundary layer Tunnel

Research focus

Our research activities focus on fundamental and applied experimental research on complicated flow problems and interactions, which affect the operation of flying vehicles - from UAVs to air-breathing hypersonic vehicles. The broad range of our current research topics covered includes:

  • Thrust vectoring
  • Shock-boundary layer interaction
  • Flow separation control
  • Surface friction drag reduction
  • Aircraft noise and emissions
  • Development of flow diagnostic techniques
  • Development and demonstration of flow and load control actuators

Experimental facilities

Our wind tunnel facilities cover the speed range from subsonic to hypersonic flow. Some of them are unique in the country. Our major wind tunnel facilities include:

  • Mach 6 hypersonic wind tunnel with a run time of 7sec
  • Transonic/supersonic wind tunnel(Mach number: 0.8 - 1.9)
  • 1.2m x 0.3m x 5m boundary layer tunnel
  • 1.0m x 1.0m x 5m blow-down wind tunnel
  • 1.2m x 0.9m x 2m blow-downwind tunnel
  • 0.5m x 0.5m x 2m closed-return water tunnel
  • 0.5m x 0.3m x 5m tilting flume

We also have the instrumentation and technical skills to undertake a wide range of high-quality point, surface and field measurements. Our measurement capabilities include:

  • Temporally-resolved high-spatial resolution near-wall velocity measurements (one, two or three velocity-component hot-wire anemometry and laser Doppler anemometry)
  • High-speed schlieren visualisation
  • Full-surface temperature and pressure measurements (temperature-and pressure-sensitive paints)
  • Scalar field measurements (Planar laser-induced fluorescent)
  • High-spatial resolution velocity measurements (2D and stereo Particle-image velocimetry) 

Vortical structures produced by synthetic jets reconstructed from stereo PIV data

Vortical structures produced by synthetic jets reconstructed from stereo PIV data

2D Velocity vector field of synthetic jets obtained with PIV

2D Velocity vector field of synthetic jets obtained with PIV

Schlieren flow visualidsation of 
supersonic thrust vectoring

Schlieren flow visualidsation of supersonic thrust vectoring

People

Academic Staff:  Dr William Crowther, Dr Antonino Filippone, Dr Shan Zhong

Please contact one of the academic staff for further details of current research activity.

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