2017
DOI: 10.3390/en10111900
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Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight

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 tw… Show more

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Cited by 16 publications
(31 citation statements)
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“…In the present paper, a concept aircraft was powered by a combined cycle hypersonic propulsion system which features a gas turbine, ramjet, and scramjet layout, and was first presented in Reference [5]. The focus was on maximising the thrust component from the ramjet as an important criterion and pre-cursor to allowing the aircraft to achieve hypersonic speeds.…”
Section: Hypersonic Propulsionmentioning
confidence: 99%
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“…In the present paper, a concept aircraft was powered by a combined cycle hypersonic propulsion system which features a gas turbine, ramjet, and scramjet layout, and was first presented in Reference [5]. The focus was on maximising the thrust component from the ramjet as an important criterion and pre-cursor to allowing the aircraft to achieve hypersonic speeds.…”
Section: Hypersonic Propulsionmentioning
confidence: 99%
“…A feasible combination of a dual-mode ramjet-scramjet is given by Figure 2, such that during high-altitude scramjet flight the ramjet inlets are sealed to prevent excessive drag induced by shockwaves on the ramjet forebody [5]. The requirement from this aircraft was for sustained Mach 8 cruise flight for a substantial part of the flight envelope with the ramjets assisting during phases 2 and 3 of the flight envelope (Table 1).…”
Section: Concept Aircraft Specificationmentioning
confidence: 99%
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