Shock wave diffraction in the presence of a supersonic co-flow jet

Gnani, F., Lo, K. H., Zare-Behtash, H. and Kontis, K. (2016) Shock wave diffraction in the presence of a supersonic co-flow jet. Shock Waves, 26(3), pp. 253-262. (doi: 10.1007/s00193-016-0634-3)

118541.pdf - Accepted Version



The interaction between a diffracting shock wave and a uniform jet is a case that so far has only been partially investigated. This interaction is extremely important for the control of noise generation and improvement of combustor performance. To fill this knowledge gap, three geometries of the diffracting corner, namely a straight ramp, a serrated ramp, and a rounded corner, have been tested experimentally to study the interaction of shock diffraction with a supersonic co-flow jet at incident Mach numbers of 1.31 and 1.59, with Reynolds numbers of 1.08×1061.08×106 and 1.68×1061.68×106, respectively. Schlieren photography was employed to analyse the evolution of the flow phenomena. The aim is to provide a qualitative understanding of the interaction between the diffracting shock wave and the uniform jet relevant to future high-speed transport. The results show that the flow field evolves more rapidly and develops stronger structures for a higher shock Mach number. The diffraction around a rounded splitter develops a periodical vortical structure which continues after the disturbance introduced by the passage of the shock wave is removed.

Item Type:Articles
Glasgow Author(s) Enlighten ID:Gnani, Francesca and Lo, Dr Kin Hing and Zare-Behtash, Dr Hossein and Kontis, Professor Konstantinos
Authors: Gnani, F., Lo, K. H., Zare-Behtash, H., and Kontis, K.
College/School:College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Journal Name:Shock Waves
ISSN (Online):1432-2153
Copyright Holders:Copyright © 2016 Springer-Verlag
First Published:First published in Shock Waves 26(3): 253-262
Publisher Policy:Reproduced in accordance with the publisher copyright policy

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