Please use this identifier to cite or link to this item: http://bura.brunel.ac.uk/handle/2438/16065
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dc.contributor.authorPesyridis, A-
dc.contributor.authorCooper, M-
dc.date.accessioned2018-04-06T09:58:32Z-
dc.date.available2018-04-06T09:58:32Z-
dc.date.issued2017-
dc.identifier.citationApplied Sciences (Bucureşti)en_US
dc.identifier.issn1454-5101-
dc.identifier.urihttp://bura.brunel.ac.uk/handle/2438/16065-
dc.description.abstractFor the past several decades, research dealing with hypersonic flight regimes has been restricted mainly to military applications. Hypersonic transportation could be a possible and affordable solution to travel in the medium term and there is renewed interest from several private organisations for commercial exploitation in this direction. Various combined cycle propulsion configurations have been proposed and the present paper deals with implications for the nozzle component of a ramjet configuration as part of one such combined cycle propulsion configuration. An investigation was undertaken for a method of turbine-based propulsion which enables the hypersonic vehicle to take off under its own power and propel the aircraft under different mission profiles into ramjet operational Mach regimes. The present study details an optimal method of ramjet exhaust expansion to produce sufficient thrust to propel the vehicle into altitudes and Mach regimes where scramjet operation can be initiated. This aspect includes a Computational Fluid Dynamics (CFD)-based geometric study to determine the optimal configuration to provide the best thrust values. The CFD parametric analysis investigated three candidate nozzles and indicated that the dual bell nozzle design produced the highest thrust values when compared to other nozzle geometries. The altitude adaptation study also validated the effectiveness of the nozzle thrust at various altitudes without compromising its thrust-producing capabilities. Computational data were validated against published experimental data, which indicated that the computed values correlated well with the experimental data.en_US
dc.language.isoenen_US
dc.subjecthypersonicen_US
dc.subjectpropulsionen_US
dc.subjectramjeten_US
dc.subjectnozzleen_US
dc.subjectconvergent-divergenten_US
dc.subjectexpansionen_US
dc.subjectshock waveen_US
dc.titleRamjet Nozzle Analysis for Transport Aircraft Configuration for Sustained Hypersonic Flighten_US
dc.typeArticleen_US
dc.relation.isPartOfApplied Sciences (Bucureşti)-
pubs.publication-statusAccepted-
Appears in Collections:Dept of Mechanical and Aerospace Engineering Research Papers

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