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Supersonic cooling by shock–vortex interaction

Published online by Cambridge University Press:  26 April 2006

M. D. Fox  and
M. Kurosaka
M. D. Fox
Affiliation:
Department of Aeronautics and Astronautics, University of Washington, Seattle, WA 98195-2400, USA Present address: Solar Turbines Inc., San Diego, CA 92186-5376, USA.
M. Kurosaka
Affiliation:
Department of Aeronautics and Astronautics, University of Washington, Seattle, WA 98195-2400, USA
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Abstract

The subject of total temperature separation in jets was treated in Fox et al. (1993) for subsonic jets. When we extended this study to the case of supersonic jets, we found the presence of a different mechanism of cooling, an effect which does not appear to have been known in the past. Named the ‘shock-induced total temperature separation’, this cooling can be of much greater magnitude than the subsonic cooling treated previously; it is caused by the interaction of convected vortical structures near the jet exhaust with the shock structure of the supersonic jet.

In studying this phenomenon, we focus our attention on overexpanded jets exiting a convergent-divergent nozzle. The theoretical results for the shock-induced cooling which are based on a linearized, unsteady supersonic analysis are shown to agree favourably with experiments.

When an impingement plate is inserted, the shock-induced cooling would manifest itself as wall cooling, whose magnitude is significantly larger than the subsonic counterpart. This has implications for heat transfer not only in jets, but wherever vortical structures may interact with shock waves.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 308 , 10 February 1996 , pp. 363 - 379
Copyright
© 1996 Cambridge University Press

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