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Oblique Shock Control with Steady Flexible Panels

Nicolas Gomez-Vega

Imperial College London, London, England SW7 2AZ, United Kingdom

*Graduate, Department of Aeronautics.

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Michela Gramola

Imperial College London, London, England SW7 2AZ, United Kingdom

†Ph.D. Candidate, Department of Aeronautics. Student Member AIAA.

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and

Paul J. K. Bruce

Imperial College London, London, England SW7 2AZ, United Kingdom

‡Reader, Department of Aeronautics. Senior Member AIAA.

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Published Online:28 Feb 2020https://doi.org/10.2514/1.J058933

Abstract

Flexible panels deforming under pressure loads have been suggested as a passive form of adaptive oblique shock control. This study investigates oblique shock–boundary-layer interactions on a steady flexible panel in a Mach 2.0 flow. Experiments were performed in the Imperial College supersonic wind tunnel, where shock generators were used to produce an oblique shock followed by a corner expansion. A parametric study was conducted, exploring different shock impingement positions and shock–expansion distances. The steady aerostructural response is studied using schlieren photography, static pressure distributions, photogrammetry measurements, and surface oil flow visualization. Two-dimensional numerical simulations were performed to assess the effects of the flexible panel on downstream total pressure recovery. These were validated against experimental wall pressure distributions and measurements from a Pitot rake. Results show reductions in both separation length (of up to 40%) and stagnation pressure losses (of up to 10%) if the flexible plate is used. These improvements occur for a range of shock positions spanning approximately 50% of the panel length and for all the shock–expansion distances considered. A model that captures the flow physics responsible for these trends is proposed. The results highlight the potential of flexible panels for practical oblique shock control.

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Volume 58, Number 5May 2020

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Copyright © 2020 by Nicolas Gomez-Vega, Michela Gramola, and Paul J. K. Bruce. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.

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Acknowledgments

The second author would like to acknowledge the Imperial College President’s PhD Scholarship Scheme, supported by Engineering and Physical Sciences Research Council, for their support of this research. The authors wish to acknowledge Dilaksan Thillaithevan for his assistance with the experimental testing.

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Received6 August 2019
Accepted2 February 2020
Published online28 February 2020

Oblique Shock Control with Steady Flexible Panels

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