Detonation Wave Mach Number Dependence In A High Mach Number Flows

Abstract

The paper presents a study of detonation propagation in supersonic crossflows over a range of Mach numbers. The work is focused on characterizing the detonation wave dependence on the supersonic cross-stream Mach number. A high-enthalpy combustor is used to provide continuous premixed supersonic crossflows that interact with an orthogonal detonation provided by a miniaturized detonation tube. The detonation wave propagation and interaction are characterized for various degrees of nozzle overexpansion driven by change in stagnation pressures. High speed Schlieren imaging is used to visualize the differences in propagating mechanisms for the detonation wave at each Mach number.

Publication Date

1-1-2018

Publication Title

22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference

Document Type

Article; Proceedings Paper

Personal Identifier

scopus

DOI Link

https://doi.org/10.2514/6.2018-5378

Socpus ID

85056108050 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/85056108050

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