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Wind-tunnel interference effects on a 70° delta wing

Part of: 75 year anniversary of Aeronautical Engineering at Glasgow University

Published online by Cambridge University Press:  03 February 2016

M. R. Allan ,
K. J. Badcock ,
G. N. Barakos  and
B. E. Richards
M. R. Allan
Affiliation:
Computational Fluid Dynamics Laboratory, Department of Aerospace Engineering, University of Glasgow, UK
K. J. Badcock
Affiliation:
Computational Fluid Dynamics Laboratory, Department of Aerospace Engineering, University of Glasgow, UK
G. N. Barakos
Affiliation:
Computational Fluid Dynamics Laboratory, Department of Aerospace Engineering, University of Glasgow, UK
B. E. Richards
Affiliation:
Computational Fluid Dynamics Laboratory, Department of Aerospace Engineering, University of Glasgow, UK
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Abstract

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This paper considers the effects of both wind-tunnel walls and a downstream support structure, on the aerodynamics of a 70° delta wing. A RANS model of the flow was used with the wind-tunnel walls and supports being modelled with inviscid wall boundary conditions. A consistent discretisation of the domain was employed such that grid dependence effects were consistent in all solutions, thus any differences occurring were due to varying boundary conditions (wall and support locations). Comparing solutions from wind-tunnel simulations and simulations with farfield conditions, it has been shown that the presence of tunnel walls moves the vortex breakdown location upstream. It has also been seen that vortex strength, helix angle, and mean incidence also increase, leading to a more upstream breakdown location in wind-tunnels. The secondary separation line was also observed to move outboards. It was observed that for high Reynolds numbers, with a support downstream of the wing, vortex breakdown can be delayed due to blockage effects providing the vortices do not impinge on the support This was observed to be the case for smaller supports also.

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1088 , October 2004 , pp. 505 - 513
Copyright
Copyright © Royal Aeronautical Society 2004 

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