Flow studies at hypersonic speeds

dc.contributor.authorBabinsky, Holgeren_UK
dc.date1991en_UK
dc.date.accessioned2005-11-23T12:20:01Z
dc.date.available2005-11-23T12:20:01Z
dc.date.issued1991en_UK
dc.description.abstractApproximate methods for calculating the surface pressures including the effects of viscous interactionare introduced for laminar and turbulent boundary layers. Experiments were performed with various models taking Schlieren pictures and pressure measurements. The flow over a two-dimensional compression corner showed transitional separation and were in agreement with other authors. The investigation of the flow over a delta wing with trailing edge flaps and body showed an influence of transition on the shape of the separated area, the pressure measurements were compared with various two-dimensional approximations. The experiments of a flow in the junction between a circular cylinder and a flat plate showed the influence of the sweep angle on the size of the separated region.en_UK
dc.description.sponsorshipThe Universityen_UK
dc.format.extent1963 bytes
dc.format.extent1377748 bytes
dc.format.mimetypetext/plain
dc.format.mimetypeapplication/pdf
dc.identifier.urihttp://hdl.handle.net/1826/212
dc.language.isoen_UKen_UK
dc.relation.ispartofseriesCollege of Aeronautics Report;9407en_UK
dc.relation.ispartofseriesCU/CoA/R;9407en_UK
dc.titleFlow studies at hypersonic speedsen_UK
dc.typeTechnical Reporten_UK

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