Control of flow separation on a contour bump by jets in a Mach 1.9 free-stream: an experimental study
Control of flow separation on a contour bump by jets in a Mach 1.9 free-stream: an experimental study
Flow separation control over a three-dimensional contour bump using jet in a Mach 1.9 supersonic free-stream has been experimentally investigated using a transonic/supersonic wind tunnel. Jet total pressure in the range of 0–4 bar was blowing at the valley of the contour bump. Schlieren photography, surface oil flow visualisation and particle image velocimetry measurements were employed for flow visualisation and diagnostics. Experimental results show that blowing jet at the valley of the contour bump can hinder the formation and distort the spanwise vortices. The blowing jet can also reduce the extent of flow separation appears downstream of the bump crest. It was observed that this approach of flow control is more effective when high jet total pressure is employed. It is believed that a pressure gradient is generated as a result of the interaction between the flow downstream of the bump crest and the jet induced shock leads to the downwards flow motion around the bump valley.
229-242
Lo, Kin Hing
475d119e-782f-4662-822d-dbcff29b8800
Zare-Behtash, Hossein
74be9b97-cb09-49c6-9f75-7ec58c0dd16c
Kontis, Konstantinos
8e534eab-6495-4dcb-ab48-e2a8906bcd8a
7 May 2016
Lo, Kin Hing
475d119e-782f-4662-822d-dbcff29b8800
Zare-Behtash, Hossein
74be9b97-cb09-49c6-9f75-7ec58c0dd16c
Kontis, Konstantinos
8e534eab-6495-4dcb-ab48-e2a8906bcd8a
Lo, Kin Hing, Zare-Behtash, Hossein and Kontis, Konstantinos
(2016)
Control of flow separation on a contour bump by jets in a Mach 1.9 free-stream: an experimental study.
Acta Astronautica, 126, .
(doi:10.1016/j.actaastro.2016.04.033).
Abstract
Flow separation control over a three-dimensional contour bump using jet in a Mach 1.9 supersonic free-stream has been experimentally investigated using a transonic/supersonic wind tunnel. Jet total pressure in the range of 0–4 bar was blowing at the valley of the contour bump. Schlieren photography, surface oil flow visualisation and particle image velocimetry measurements were employed for flow visualisation and diagnostics. Experimental results show that blowing jet at the valley of the contour bump can hinder the formation and distort the spanwise vortices. The blowing jet can also reduce the extent of flow separation appears downstream of the bump crest. It was observed that this approach of flow control is more effective when high jet total pressure is employed. It is believed that a pressure gradient is generated as a result of the interaction between the flow downstream of the bump crest and the jet induced shock leads to the downwards flow motion around the bump valley.
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Accepted/In Press date: 12 April 2016
e-pub ahead of print date: 28 April 2016
Published date: 7 May 2016
Identifiers
Local EPrints ID: 490944
URI: http://eprints.soton.ac.uk/id/eprint/490944
ISSN: 0094-5765
PURE UUID: 2306dfd2-8c0b-4a98-b707-4480b459709b
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Date deposited: 10 Jun 2024 16:34
Last modified: 11 Jun 2024 02:09
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Author:
Kin Hing Lo
Author:
Hossein Zare-Behtash
Author:
Konstantinos Kontis
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