A5085731770- Aerodynamics and Fluid Dynamics Research
- Wind and Air Flow Studies
- Fluid Dynamics and Turbulent Flows
- Vehicle emissions and performance
- Computational Fluid Dynamics and Aerodynamics
- Fluid Dynamics and Vibration Analysis
- Aerodynamics and Acoustics in Jet Flows
- Combustion and flame dynamics
- Aerospace and Aviation Technology
- Gas Dynamics and Kinetic Theory
- Plasma and Flow Control in Aerodynamics
- Vehicle Noise and Vibration Control
- Advanced Fiber Optic Sensors
- Engineering Applied Research
- Traffic control and management
- Turbomachinery Performance and Optimization
- Advanced Fiber Laser Technologies
- Particle Dynamics in Fluid Flows
- Heat Transfer Mechanisms
- Vehicle Dynamics and Control Systems
- Advanced Aircraft Design and Technologies
- Heat Transfer and Optimization
- Surgical Simulation and Training
- Air Traffic Management and Optimization
- Lightning and Electromagnetic Phenomena
Cranfield University
2012-2025
Royal Victoria Eye and Ear Hospital
2018
Vaughn College of Aeronautics and Technology
1985-2002
Fibre optic based sensors are becoming increasingly viable as replacements for traditional flight test sensors. Here we present laboratory, wind tunnel and results of fibre Bragg gratings (FBG) used to measure surface strain an extrinsic Fabry–Perot interferometric (EFFPI) sensor unsteady pressure. The calibrated full scale resolution bandwidth the FBG EFFPI were shown be 0.29% at 2.5 kHz up 600 με 0.15% 10 respectively 400 Pa. tests, completed on a 30% model, allowed developed before...
A new method to measure shock wave unsteadiness is presented. Time-resolved visualizations of the flow field under investigation are obtained using a high-speed schlieren optical system and motion determined by means digital image processing. Information on shock's subsequently derived with Fourier analysis. sample study in shock-wave/turbulent boundary-layer interaction separation included. The presented enables at locations imaged not accessible intrusive methods.
Experimental investigation is essential to improve the understanding of aerospace flows. During last years, effort has been put on development optical diagnostics capable imaging or yielding data from flow in a nonintrusive way. The application some these techniques supersonic and hypersonic flows can be highly challenging due high velocity, strong gradients, restricted access generally encountered. Widely used qualitative semiquantitative are shadowgraph, schlieren, interferometry....
The results of an experimental investigation the bootdeck flow structure a 36 per cent scale model notchback car are presented together with general review advanced laser diagnostic techniques suitable for large-scale wind tunnel measurement. tests were used to characterize behaviour over Reynolds number range 0.74 × 10 6 -4.93 in Cranfield University 2.4 m 1.8 tunnel. experiments involved visualization, rear and backlight three-dimensional stereoscopic particle image velocimetry (PIV)...
Experimental results of static pressure measurements from specially packaged π-phase shifted optical fibre Bragg gratings (FBGs) that were installed into a 2D, 3 element high lift wing are presented. The the sensors found to be in good agreement with theory. Further calibrations currently under investigation.
Abstract The vorticity production by a single vortex generator jet in turbulent boundary layer at high speed and zero pressure gradient was studied analysing surface-flow patterns. investigation involved range of mass flow rates skew angles while the freestream Mach number pitch angle were held constant. A qualitative analysis skin friction patterns demonstrated effective role as bifurcation parameter. is classified into three main regimes increases from (fully downstream) to 180° upstream)....
Abstract An experimental and numerical study was performed on a Clark Y aerofoil with 10% chord leading edge Kruger flap to examine its aerodynamic performance at Reynolds numbers of 0·6 × 10 6 , 1 1·6 help identify the forces moments acting basic configuration. A detailed comparison data is presented in this paper. The effective high angles attack an increase C L up 18% over conventional no configuration delayed separation by 3°. around rotation point were calculated from analysis as...
A modern benchmark for passenger cars -DrivAer modelhas provided significant contributions to aerodynamics-related topics in automotive engineering, where three categories of have been successfully represented.However, a reference model highperformance car configurations has not considered appropriately yet.Technical knowledge motorsport is also restricted due competitiveness performance, reputation and commercial gains.The consequence shortage open-access material be used as technical...
Abstract Shock-wave/turbulent boundary-layer interactions (SWTBLIs) with separation are known to be inherently unsteady but their physical mechanisms still not totally understood. An experimental investigation has been performed in a supersonic wind tunnel at freestream flow Mach number of 2·42. The interaction between shock wave created by generator (α = 3°, α 9°, 13° and 15° deflection angles) turbulent boundary layer thickness δ 5mm studied. High-speed Schlieren visualisations have...