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dc.contributor.advisorLewis, Mark Jen_US
dc.contributor.authorChauffour, Marie-Laureen_US
dc.date.accessioned2004-08-27T05:38:04Z
dc.date.available2004-08-27T05:38:04Z
dc.date.issued2004-08-10en_US
dc.identifier.urihttp://hdl.handle.net/1903/1829
dc.description.abstractWaveriders demonstrate good aerodynamic performance and thus are of special interest for hypersonic applications, especially for engine-airframe integration. The osculating cones waverider method is a generic shock-based derived waverider design method that allows prescribing a wide variety of flowfields at the inlet of the engine of the hypersonic vehicle. Previous osculating cones waveriders methods assumed that along the streamlines within the waverider shock layer, the pressure gradients in the azimuthal direction were negligible, and thus neglected it into the design process. The focus of this work is to investigate the magnitude of those pressure gradients, and integrate those into a new osculating cones waverider design method by modifying the derivation of the lower surface (streamsurface). The geometries resulting from the design code are to be compared with the previous solutions. The flowfield and aerodynamic performance predicted by the design code are compared with the results from Computational Fluid Dynamics simulations.en_US
dc.format.extent7199912 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.titleShock-Based Waverider Design with Pressure Gradient Corrections and Computational Simulationsen_US
dc.typeThesisen_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.pqcontrolledEngineering, Aerospaceen_US


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