Details of Grant 

EPSRC Reference:	GR/R17867/01
Title:	Travel Grant To Attend An International Activity On Vortex Breakdown
Principal Investigator:	Gursul, Professor I
Other Investigators:
Researcher Co-Investigators:
Project Partners:
Department:	Mechanical Engineering
Organisation:	University of Bath
Scheme:	Overseas Travel Grants Pre-FEC
Starts:	08 March 2001	Ends:	07 March 2003	Value (£):	3,847
EPSRC Research Topic Classifications:	Aerodynamics
EPSRC Industrial Sector Classifications:	Aerospace, Defence and Marine
Related Grants:
Panel History:
Summary on Grant Application Form
Vortex flows are of obvious importance for military applications concerning combat aircraft as well as for future high-speed civil transport employing rouble delta wing planforms. At a sufficiently high angle of attack, the vortices undergo a sudden expansion known as vortex breakdown, which has adverse effects on the aircraft performance, stability and control, and causes wing/fin buffeting. Experimental investigations show that large scatter appears in the experimental results, especially in the vortex breakdown location. Geometric variations, tunnel wall effects, support interference, model deformations, Reynolds number, measurement technique, and unsteady nature of breakdown are all possible sources of the large scatter. These factors significantly affect the usefulness of the experimental data for aerodynamic analysis and design. Thus the clarification of these data sets would increase the usefulness of the database, which can be used in the design of new aircraft. It is also obvious that benchmark experiments need to be designed with well-defined model geometry and boundary conditions. The main objective of this NATO activity to compile, compare, and explain the experimental results on vortex breakdown over slender wings, which presently show a large scatter of data. The second objective is to validate different computational fluid dynamics (CFD) codes with well-defined benchmark experiments. In addition, the study will cover large range of Reynolds numbers including low Reynolds regime. Therefore it is expected to be applicable to some micro air vehicle (MAV) shapes with longitudinal vortices.
Key Findings
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Organisation Website:	http://www.bath.ac.uk