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Passive control of pre-entry shock in supersonic intakes

Published online by Cambridge University Press:  04 July 2016

S.C. Rolston  and
S. Raghunathan
S.C. Rolston
Affiliation:
Department of Aeronautical EngineeringThe Queen's University of Belfast
S. Raghunathan
Affiliation:
Department of Aeronautical EngineeringThe Queen's University of Belfast
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Abstract

Passive boundary layer control experiments were conducted on a small supersonic sidewall intake at a Mach number of 1·46 to study the possibility of controlling and improving the intake performance by such a control. The passive control configurations tested included a suction slot in the intake duct located down stream of the shock system (1) connected by a breather passage to a narrow tangential injection slot upstream of the intake and (2) vented to a location where the pressure is free stream static pressure and well away from the inlet of the intake. The results of the experiments showed, that for a supersonic intake, passive control can control the pre-entry shock position, reduce the shock interaction losses and improve the overall pressure recovery.

Type
Research Article
Information
The Aeronautical Journal , Volume 98 , Issue 971 , January 1994 , pp. 1 - 8
Copyright
Copyright © Royal Aeronautical Society 1994 

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