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Passive control of shock wave–boundary-layer interactions

Published online by Cambridge University Press:  04 July 2016

T. M. Gibson ,
H. Babinsky  and
L. C. Squire
T. M. Gibson
Affiliation:
Aerodynamics Laboratory, Cambridge University Engineering Department, Cambridge, UK
H. Babinsky
Affiliation:
Aerodynamics Laboratory, Cambridge University Engineering Department, Cambridge, UK
L. C. Squire
Affiliation:
Aerodynamics Laboratory, Cambridge University Engineering Department, Cambridge, UK
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Abstract

The passive control of a shock wave-boundary-layer interaction involves placing a porous surface beneath the interaction, allowing high pressure air from the flow downstream of the shock wave to recirculate through a plenum chamber into the low pressure flow upstream of the wave.

The simple case of a normal shock wave at a Mach number of 1·4 interacting with the turbulent boundary layer on a flat wall is investigated both experimentally and numerically. The experimental investigation made use of holographic interferometry, while the computational section of the investigation made use of a Navier-Stokes code to derive pressure gradients, boundary-layer properties and total pressure losses in the interaction region. It is found that the structure of shock wave-boundary-layer interactions with passive control consists of a leading, oblique shock wave followed by a lambda foot. The oblique wave originates from the upstream end of the porous region, and its strength is determined by the magnitude of the local blowing velocities. The shape of the lambda foot depends on the position of the main shock relative to the control region, resembling an uncontrolled foot when the main shock wave is towards the downstream end of the porosity, but becoming increasingly large as the shock moves upstream and eventually merging with the leading, oblique shock to form a single, large, lambda structure.

Improved forms of passive control are suggested based on the findings of this investigation, including the use of passive control systems which incorporate streamwise variations in the level of porosity.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1033 , March 2000 , pp. 129 - 140
Copyright
Copyright © Royal Aeronautical Society 2000 

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