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Simulation of Dual-Mode Scramjet Under Thermally Choked vs. Supersonic Combustion Mode

dc.contributor.advisorYu, Kenneth Hen_US
dc.contributor.authorButcher, Cameronen_US
dc.description.abstractEffects of combustion mode and cavity flame-holder on dual-mode scramjet performance were investigated using a two-dimensional computational framework developed from commercial finite element software. The objectives were to simulate the experimental data from a laboratory model scramjet with mixing enhancement device, provide better understanding of the physical processes, and to analyze the quantitative effects on the potential performance. The isolator flow field was modeled separately to match the experimentally obtained pressure rise during the Mach 2.1 isolator entry condition. The combustor heat release distribution was systematically adjusted to reproduce the wall pressure distributions from the experiments. Case studies were conducted with and without the presence of the wall cavity for scramjet operation under both thermally-choked and supersonic-combustion mode. The combustion mode affected potential tradeoffs between thrust increase and higher thermal protection need. The presence of the cavity dampened the extent of the tradeoffs by reducing the temperature change.en_US
dc.titleSimulation of Dual-Mode Scramjet Under Thermally Choked vs. Supersonic Combustion Modeen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.contributor.departmentAerospace Engineeringen_US
dc.subject.pqcontrolledAerospace engineeringen_US
dc.subject.pquncontrolledDual-mode scramjeten_US

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