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dc.contributor.advisorLewis, Mark J.en_US
dc.contributor.authorBussey, Gillian Mary Hardingen_US
dc.date.accessioned2010-07-02T05:35:06Z
dc.date.available2010-07-02T05:35:06Z
dc.date.issued2009en_US
dc.identifier.urihttp://hdl.handle.net/1903/10231
dc.description.abstractA method for correcting flow non-uniformities and incorporating multiple oblique shocks waves into compound compressible flow is presented. This method has several applications and is specifically presented for the problem of creating a streamline-traced hypersonic three-dimensional inlet. This method uses compound compressible flow theory to solve for the freestream flow entering a pre-defined duct with a desired downstream profile. This method allows for multiple iterations of the design space and is computational inexpensive. A method is also presented for modeling a laminar or turbulent boundary layer to compare inlet designs and to determine the viscous correction to the inlet. Two different Mach 6 designs were evaluated, with a rectangular capture area and circular combustor with a uniform temperature, pressure, and Mach number profile. Comparison with other three-dimensional inlets indicates those designed with this method demonstrate good inviscid performance. These inlets also have the ability to correct incoming flow non-uniformities.en_US
dc.titleApplication of Compound Compressible Flow to Hypersonic Three-Dimensional Inletsen_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
dc.subject.pquncontrolledcompound compressibleen_US
dc.subject.pquncontrolledhypersonicsen_US
dc.subject.pquncontrolledinletsen_US
dc.subject.pquncontrolledinward-turningen_US
dc.subject.pquncontrolledscramjetsen_US


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