Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight

Through Computational Fluid Dynamics and validation, an optimal scramjet combustor has been designed based on twin-strut Hydrogen injection to sustain flight at a desired speed of Mach 8. An investigation undertaken into the efficacy of supersonic combustion through various means of injection saw pr...

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Bibliographic Details

Published in:	Energies
Main Authors:	Stephen M. Neill, Apostolos Pesyridis
Format:	Article
Language:	English
Published:	MDPI AG 2017-11-01
Subjects:	supersonic combustion hypersonic scramjet propulsion fuel injection computational fluid dynamics
Online Access:	https://www.mdpi.com/1996-1073/10/11/1900