Propagation Of A Detonation Wave In Supersonic Crossflows Using A Pre-Detonator

Keywords

Chapman-Jouguet detonation wave; Detonation wave; Hypersonic Combustor; Mach 5; Schlieren imaging

Abstract

Detonation wave propagation in a hypersonic cross-flow wind tunnel was examined. Detonation waves are waves with a sonic condition behind the shock front and remain an unexplored area with a growing demand for technological applications in hypersonic aircraft. The objective of this work is to investigate the evolution of a detonation wave in a Mach 5 crossflow with varying CJ detonation conditions and observe the under-driven, over-driven, and quasi-stable propagation of the detonation wave. Initial reactant temperature and equivalence ratio are varied to tailor the CJ detonation conditions in the supersonic free stream. The current high-enthalpy combustor provides cross-flow Mach numbers up to Mach 5 and stagnation temperatures up to 1100K. A H2/O2 pre-detonator placed orthogonally to the supersonic free stream is used to initiate the detonation wave. High speed Schlieren imaging is utilized to observe the wave transfer from the pre-detonator to the supersonic mixture and understand detonation propagation mechanisms in a Mach 5 flow.

Publication Date

1-1-2018

Publication Title

Proceedings of the Thermal and Fluids Engineering Summer Conference

Volume

2018-March

Number of Pages

67-70

Document Type

Article; Proceedings Paper

Personal Identifier

scopus

DOI Link

https://doi.org/10.1615/TFEC2018.asp.021715

Socpus ID

85090786742 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/85090786742

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