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Investigation of active control of swept shock wave/turbulent boundary-layer interactions – PSP results

Published online by Cambridge University Press:  03 February 2016

J. S. Couldrick ,
S. L. Gai ,
J. F. Milthorpe  and
K. Shankar
J. S. Couldrick
Affiliation:
School of Aerospace, Civil and Mechanical Engineering, University College, UNSW, Australian Defence Force Academy, Canberra, Australia
S. L. Gai
Affiliation:
School of Aerospace, Civil and Mechanical Engineering, University College, UNSW, Australian Defence Force Academy, Canberra, Australia
J. F. Milthorpe
Affiliation:
School of Aerospace, Civil and Mechanical Engineering, University College, UNSW, Australian Defence Force Academy, Canberra, Australia
K. Shankar
Affiliation:
School of Aerospace, Civil and Mechanical Engineering, University College, UNSW, Australian Defence Force Academy, Canberra, Australia
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Abstract

An investigation of active control of the swept shock wave/boundary-layer interaction using ‘smart’ flap actuators is presented. The actuators are manufactured by bonding piezoelectric material to an inert substrate to control the bLeed/suction rate through a plenum chamber. The cavity provides communication of signals across the shock, allowing rapid thickening of the boundary layer approaching the shock. This splits the shock foot into a series of weaker shocks forming a lambda structure, thus reducing wave drag. Active control allows optimisation of the unimorph deflection, hence rate of mass transfer.

In this paper, results of the interaction using pressure sensitive paint (PSP) are emphasised. It is shown that the use of PSP, in conjunction with discrete pressure data, enables the main features of the interaction to be observed when the actuators are subject to different deflections.

Type
Technical Note
Information
The Aeronautical Journal , Volume 108 , Issue 1087 , September 2004 , pp. 483 - 490
Copyright
Copyright © Royal Aeronautical Society 2004 

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