Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight

Stephen M. Neill and Apostolos Pesyridis
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Stephen M. Neill: Aerospace Engineering Graduate, College of Engineering and Design, Brunel University London, Uxbridge UB8 3PN, UK
Apostolos Pesyridis: Metapulsion Engineering Ltd, 2C Eastbury Avenue, Northwood HA6 3LG, UK

Energies, 2017, vol. 10, issue 11, 1-22

Abstract: 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 promising results for Hydrogen-based systems, whereby strut-style injectors were selected over transverse injectors based on their pressure recovery performance and combustive efficiency. The final configuration of twin-strut injectors provided robust combustion and a stable region of net thrust (1873 kN) in the nozzle. Using fixed combustor inlet parameters and injection equivalence ratio, the finalized injection method advanced to the early stages of two-dimensional (2-D) and three-dimensional (3-D) scramjet engine integration. The overall investigation provided a feasible supersonic combustion system, such that Mach 8 sustained cruise could be achieved by the aircraft concept in a computational design domain.

Keywords: supersonic combustion; hypersonic; scramjet; propulsion; fuel injection; computational fluid dynamics (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2017
References: View complete reference list from CitEc
Citations: View citations in EconPapers (5)

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