Integrating hypersonics into a combustion test facility with 3D viewing capability

Sevcenco, Yura ORCID: https://orcid.org/0000-0002-6489-9903, Mojarrad, Mehrshad, Marsh, Richard ORCID: https://orcid.org/0000-0003-2110-5744, Morris, Steven ORCID: https://orcid.org/0000-0001-5865-8911, Bowen, Philip John ORCID: https://orcid.org/0000-0002-3644-6878 and Syred, Nicholas 2015. Integrating hypersonics into a combustion test facility with 3D viewing capability. Presented at: 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Glasgow, UK, 6-9 Jul, 2015. 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. American Institute of Aeronautics and Astronautics, 10.2514/6.2015-3654

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Abstract

This describes the evolution of a high pressure combustion rig with viewing capability from 3 dimensions to add functionality for hypersonic testing. The design target is for supersonic combustion and hypersonic flow characterisation. One of the current major features of the existing combustion rig is the ability to carry out full 3D studies via the use of an extra optical window which allows flow and other parameter characterization in the rθ direction. Non intrusive laser diagnostics have been installed to use this, with the analysis shown with dynamic pressure transducers to give thermoacoustic relevance to the heat release detection capability.

Item Type:	Conference or Workshop Item (Paper)
Date Type:	Publication
Status:	Published
Schools:	Engineering
Subjects:	T Technology > TJ Mechanical engineering and machinery T Technology > TL Motor vehicles. Aeronautics. Astronautics
Publisher:	American Institute of Aeronautics and Astronautics
ISBN:	9781624103209
Last Modified:	16 Nov 2022 08:11
URI:	https://orca.cardiff.ac.uk/id/eprint/76491

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