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Energies 2017, 10(11), 1900; https://doi.org/10.3390/en10111900

Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight

1
Aerospace Engineering Graduate, College of Engineering and Design, Brunel University London, Uxbridge UB8 3PN, UK
2
Metapulsion Engineering Ltd, 2C Eastbury Avenue, Northwood HA6 3LG, UK
*
Author to whom correspondence should be addressed.
Received: 16 October 2017 / Revised: 8 November 2017 / Accepted: 9 November 2017 / Published: 18 November 2017

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. View Full-Text
Keywords: supersonic combustion; hypersonic; scramjet; propulsion; fuel injection; computational fluid dynamics supersonic combustion; hypersonic; scramjet; propulsion; fuel injection; computational fluid dynamics
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Neill, S.M.; Pesyridis, A. Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight. Energies 2017, 10, 1900.

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