A calculation of pressure recovery behind a normal shock in hypersonic flow

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dc.contributor.advisorBeckmann, Herbert K.
dc.creatorMurray, Robert H
dc.date.accessioned2016-04-21T12:01:47Z
dc.date.available2016-04-21T12:01:47Z
dc.date.issued1960
dc.description.abstractAn analytical model is devised for investigating the flow immediately behind the normal shock which stands in the throat of the conical shock diffuser of a hypersonic wind tunnel. A method is developed for calculating the flow properties, specifically the static and total pressures, for the case of large heat losses to the wall. An example is worked out to illustrate the method and some typical results.
dc.format.digitalOriginreformatted digitalen_US
dc.format.extent55 ppen_US
dc.identifier.callnoThesis M.E. 1960 MURRAYen_US
dc.identifier.citationMurray, Robert H. "A calculation of pressure recovery behind a normal shock in hypersonic flow." (1960) Master’s Thesis, Rice University. <a href="https://hdl.handle.net/1911/89184">https://hdl.handle.net/1911/89184</a>.
dc.identifier.digitalRICE0221en_US
dc.identifier.urihttps://hdl.handle.net/1911/89184
dc.language.isoeng
dc.rightsCopyright is held by the author, unless otherwise indicated. Permission to reuse, publish, or reproduce the work beyond the bounds of fair use or other exemptions to copyright law must be obtained from the copyright holder.
dc.titleA calculation of pressure recovery behind a normal shock in hypersonic flow
dc.typeThesis
dc.type.materialText
thesis.degree.departmentMechanical Engineering
thesis.degree.disciplineEngineering
thesis.degree.grantorRice University
thesis.degree.levelMasters
thesis.degree.nameMaster of Science
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