Advances On The Stabilization Of Standing Continuous Detonation For Pressure Gain Propulsion

Abstract

This work outlines the recent advancements of a hypersonic combustor to study the stabilization of normal and oblique detonation waves. The current high-enthalpy combustor provides a Mach 5 flow for the study of oblique detonation wave stabilization utilizing air and hydrogen. Recent results in the advances of high pressure burning capabilities, nozzle inlet temperature measurements and supersonic flow verification via Mach wave angle measurements from Schlieren imaging are presented.

Publication Date

1-1-2017

Publication Title

53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017

Document Type

Article; Proceedings Paper

Personal Identifier

scopus

DOI Link

https://doi.org/10.2514/6.2017-4909

Socpus ID

85085850586 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/85085850586

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