Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight
AbstractThrough 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
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Neill, S.M.; Pesyridis, A. Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight. Energies 2017, 10, 1900.
Neill SM, Pesyridis A. Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight. Energies. 2017; 10(11):1900.Chicago/Turabian Style
Neill, Stephen M.; Pesyridis, Apostolos. 2017. "Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight." Energies 10, no. 11: 1900.
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