Design &Amp; Development Of A Hypersonic Combustor For Oblique Detonation Wave Stabilization

Abstract

This work outlines the concept and design of a hypersonic combustor to study the stabilization of normal and oblique detonation waves. The current challenge in detonation wave stabilization, is generating the appropriate conditions to match the Chapman-Jouguet (CJ) velocities necessary for a stable detonation while avoiding an overdriven detonation. This design proposes a Mach 5 facility with an optical access test section, with a cross sectional area of 45x45mm for the investigation of oblique detonation wave stabilization utilizing air and hydrogen to drive the reaction. The test section nozzle is the key component to achieving these conditions; an axisymmetric nozzle with a 5thorder polynomial contour for the contraction and an analytical derivative of the method of characteristics for the diverging section is presented.

Publication Date

1-1-2017

Publication Title

AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting

Document Type

Article; Proceedings Paper

Personal Identifier

scopus

DOI Link

https://doi.org/10.2514/6.2017-0371

Socpus ID

85017229334 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/85017229334

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