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(Reference retrieved automatically from Web of Science through information on FAPESP grant and its corresponding number as mentioned in the publication by the authors.)

Chemically reacting hypersonic flows over 3D cavities: Flowfield structure characterisation

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Author(s):
Palharini, Rodrigo C. [1] ; Scanlon, Thomas J. [2] ; White, Craig [3]
Total Authors: 3
Affiliation:
[1] Inst Aeronaut & Espaco, Div Aerodinam, BR-12228904 Sao Jose Dos Campos, SP - Brazil
[2] Univ Strathclyde, Dept Mech & Aerosp Engn, Glasgow G1 1XJ, Lanark - Scotland
[3] Univ Glasgow, Sch Engn, Glasgow G12 8QQ, Lanark - Scotland
Total Affiliations: 3
Document type: Journal article
Source: COMPUTERS & FLUIDS; v. 165, p. 173-187, MAR 30 2018.
Web of Science Citations: 3
Abstract

In this paper, a computational investigation of hypersonic rarefied gas flows in the transitional flow regime over 3D cavities is carried out by using the direct simulation Monte Carlo method. Such cavities give rise to geometric discontinuities that are often present at the surface of reentry vehicles. This work is focused on the flowfield structure characterisation under a rarefied environment and in the presence of chemical reactions. The cavities are investigated with different length-to-depth ratios, and the different flow structures are studied. In particular, for length-to-depth ratios of 1 and 2, a single recirculation is observed inside the cavities and the main flow is not able to enter the cavity due to the recirculation structure and high particle density. In the case of length-to-depth ratio 3, the flow is able to partially enter the cavity resulting in an elongated recirculation and the beginning of a secondary recirculation core is noticed. For the case of values 4 and 5, the main flow is able to penetrate deeper into the cavities and two recirculation zones are observed; however, for the length-to-depth ratio 5 the flow impinges directly on the bottom surface, which is a behaviour that is only observed in the continuum regime with a cavity length-to-depth ratio greater than 14. Crown Copyright (C) 2018 Published by Elsevier Ltd. All rights reserved. (AU)

FAPESP's process: 14/25438-1 - Numerical investigation of hypersonic vehicles aerothermodynamics during atmospheric re-entry under non-chemical equilibrium
Grantee:Rodrigo Cassineli Palharini
Support Opportunities: Scholarships in Brazil - Post-Doctoral