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

Shock wave diffraction in the presence of a supersonic co-flow jet
Shock wave diffraction in the presence of a supersonic co-flow jet
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 x 106 and 1,68 x 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.
1432-2153
253–262
Gnani, F.
6001364a-f3ee-400e-9394-8adb273c044a
Lo, K.H.
e2fcd08c-2efd-4cec-ad0a-92969e9d1139
Zare-Behtash, H.
74be9b97-cb09-49c6-9f75-7ec58c0dd16c
Kontis, K.
8e534eab-6495-4dcb-ab48-e2a8906bcd8a
Gnani, F.
6001364a-f3ee-400e-9394-8adb273c044a
Lo, K.H.
e2fcd08c-2efd-4cec-ad0a-92969e9d1139
Zare-Behtash, H.
74be9b97-cb09-49c6-9f75-7ec58c0dd16c
Kontis, K.
8e534eab-6495-4dcb-ab48-e2a8906bcd8a

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, 253–262. (doi:10.1007/s00193-016-0634-3).

Record type: Article

Abstract

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 x 106 and 1,68 x 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.

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Accepted/In Press date: 16 February 2016
Published date: 5 March 2016

Identifiers

Local EPrints ID: 490892
URI: http://eprints.soton.ac.uk/id/eprint/490892
ISSN: 1432-2153
PURE UUID: dfc99489-9781-4902-af4d-d39aae942b66
ORCID for H. Zare-Behtash: ORCID iD orcid.org/0000-0002-4769-4076

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Date deposited: 07 Jun 2024 17:43
Last modified: 08 Jun 2024 02:11

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Contributors

Author: F. Gnani
Author: K.H. Lo
Author: H. Zare-Behtash ORCID iD
Author: K. Kontis

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