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The effect of trailing edge geometry on cavity flow oscillation driven by a supersonic shear layer

Published online by Cambridge University Press:  04 July 2016

X. Zhang,
A. Rona and
J. A. Edwards
X. Zhang
Affiliation:
Department of Aeronautics and AstronauticsUniversity of SouthamptonSouthampton, UK
A. Rona
Affiliation:
Department of Aeronautics and AstronauticsUniversity of SouthamptonSouthampton, UK
J. A. Edwards
Affiliation:
Weapons Systems Sector, Dera Fort Halstead Sevenoaks, UK
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Abstract

A computational analysis is performed of self-sustained oscillatory flow over a cavity driven by a shear layer at Mach 1·5. The unsteady flow is studied through solutions of the Reynolds-averaged Navier-Stokes equations with turbulence modelled by a two-equation k-ω model. The trailing edge (face) of a baseline rectangular cavity is modified using wedge and ramp shapes to investigate means for the suppression and attenuation of the self-sustained oscillation. Through modification of the shear layer impingement, both wedge and ramp are effective in reducing the level of oscillation. The time-averaged pressure (form) drag coefficient of the cavity is also reduced significantly. The main cause of the drag reduction is the elimination or reduction of the high pressure area near the downstream corner of the cavity due to the presence of a vortex. Two types of unsteady flow exist when a curved ramp is employed: ‘regular’ and ‘random’. The use of a h= 0·6D ramp generates a random type pressure fluctuation with lower rms pressure compared with the h= 0·2D and 0·4D ramps.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 102 , Issue 1013 , March 1998, pp. 129 - 136
Copyright
Copyright © Royal Aeronautical Society 1998 

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