Control of flow separation on a contour bump by jets in a Mach 1.9 free-stream: an experimental study

Lo, K. H., Zare-Behtash, H. and Kontis, K. (2016) Control of flow separation on a contour bump by jets in a Mach 1.9 free-stream: an experimental study. Acta Astronautica, 126, pp. 229-242. (doi: 10.1016/j.actaastro.2016.04.033)

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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.

Item Type:Articles
Additional Information:The authors would like to acknowledge the EPSRC (Grant number: EPSRC iCASE/DSTL/MBDA 12440107) for funding this research project.
Glasgow Author(s) Enlighten ID:Kontis, Professor Konstantinos and Lo, Dr Kin Hing and Zare-Behtash, Dr Hossein
Authors: Lo, K. H., Zare-Behtash, H., and Kontis, K.
College/School:College of Science and Engineering > School of Engineering > Aerospace Sciences
Journal Name:Acta Astronautica
Published Online:28 April 2016
Copyright Holders:Copyright © 2016 IAA
First Published:First published in Acta Astronautica 126: 229-242
Publisher Policy:Reproduced under a Creative Commons License

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