Experimental investigation of sonic transverse jets in Mach 5 crossflow

Erdem, E. and Kontis, K. (2021) Experimental investigation of sonic transverse jets in Mach 5 crossflow. Aerospace Science and Technology, 110, 106419. (doi: 10.1016/j.ast.2020.106419)

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An experimental investigation of sonic transverse jets in Mach 5 cross flow over a flat plate with a sharp leading edge was carried out. Jet to free stream momentum flux ratio, J, was varied from 1.16 to 5.30. Schlieren visualisation provided information regarding mean flow features such as Mach disc height, h, separation length, Xsep as well as inherent unsteadiness. Steady wall pressure measurements diagnosed the interaction region between the jet and the incoming cross flow developing on the flat plate. To assess the jet penetration characteristics and trajectories, two-component Particle Image Velocimetry (PIV) measurements were carried out at the centreplane of the flat plate. Raw PIV image analysis was used to specify jet penetration boundaries. Ensemble-averaged streamwise and transverse velocity contours revealed the mean flow structures. The barrel shocks and the Mach disc forming the jet boundary can be easily seen and were visualised/quantified using PIV measurement technique. Maximum turbulence occurred above the Mach disc due to the presence of the shear layer and at the intersection of the windward side of the barrel shock and bow shock.

Item Type:Articles
Additional Information:This work was supported by Defence Science and Technology Laboratory, UK under contract number DSTLX 1000043546.
Glasgow Author(s) Enlighten ID:Kontis, Professor Konstantinos and Erdem, Dr Erinc
Authors: Erdem, E., and Kontis, K.
College/School:College of Science and Engineering > School of Engineering
College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Journal Name:Aerospace Science and Technology
ISSN (Online):1626-3219
Published Online:23 December 2020
Copyright Holders:Copyright © 2020 Elsevier Masson SAS
First Published:First published in Aerospace Science and Technology 110: 106419
Publisher Policy:Reproduced in accordance with the publisher copyright policy

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