THERMAL SCIENCE

International Scientific Journal

Donghui Wang

,

Shiqichang Wu

,

Yiqing Li

,

Jingwei Gao

COMPUTATIONAL INVESTIGATIONS OF THE EFFECTS OF WALL SURFACE TEMPERATURE ON A HYPERSONIC INLET ISOLATOR

ABSTRACT
Flow and shock train development in a hypersonic inlet isolator at various wall surface temperatures, Tw, and freestream static temperatures, T∞, were studied through numerical simulations. A non-dimensional parameter, Tw /T∞, is used to characterize flow behaviors in hypersonic isolator. With the increase of Tw /T∞, boundary-layer thickness increases and boundary-layer momentum thickness decreases at the entrance of isolator. Inside the isolator without the presence of backpressure, skin friction decreases with the increase of Tw /T∞. The main cause is a lower velocity gradient near the wall at high temperature. A lower skin friction on high wall temperature results in a stronger separation with shock impingement. Under backpressure conditions, with the increase of Tw /T∞, an upstream movement of the starting position of the shock train inside the isolator, an increase in the length of the shock train, and an increase in pressure coefficient on the wall surface are observed.
KEYWORDS
hypersonic inlet isolator, wall surface temperature, boundary-layer thickness, shock train
PAPER SUBMITTED: 2023-06-28
PAPER REVISED: 2023-11-26
PAPER ACCEPTED: 2023-11-26
PUBLISHED ONLINE: 2024-01-20
DOI REFERENCE: https://doi.org/10.2298/TSCI230628279W
CITATION EXPORT: view in browser or download as text file
THERMAL SCIENCE YEAR 2024, VOLUME 28, ISSUE Issue 4, PAGES [2791 - 2804]
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Computational investigations of the effects of wall surface temperature on a hypersonic inlet isolator

© 2024 Society of Thermal Engineers of Serbia. Published by the Vinča Institute of Nuclear Sciences, National Institute of the Republic of Serbia, Belgrade, Serbia. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution-NonCommercial-NoDerivs 4.0 International licence