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Active control of swept shock wave/turbulent boundary-layer interactions

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

This paper looks at active control of the swept shock wave/turbulent boundary-layer interaction using smart flap actuators. 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, which splits into a series of weaker shocks forming a lambda shock foot, reducing wave drag. Active control allows optimum control of the interaction, as it would be capable of positioning the control region around the original shock position and control the rate of mass transfer.

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1080 , February 2004 , pp. 93 - 101
Copyright
Copyright © Royal Aeronautical Society 2004 

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