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dc.contributor.authorRoth, Bryce Alexanderen_US
dc.contributor.authorMavris, Dimitri N.en_US
dc.date.accessioned2005-05-26T14:01:16Z
dc.date.available2005-05-26T14:01:16Z
dc.date.issued2000-07en_US
dc.identifier.urihttp://hdl.handle.net/1853/6307
dc.descriptionPresented at the 36th Joint Propulsion Conference and Exhibit, Huntsville, AL, July 2000.en_US
dc.description.abstractThe objective of this paper is to clarify the relationships between various work loss figures of merit that have been proposed for application to gas turbine propulsion. The intent is to provide a working comparison by way of a pedagogical example using the J-79 turbojet engine. The results of this analysis are then used to draw inferences as to what applications each work potential figure of merit is best suited. Finally, a general suggested as a guide to which of the various loss figures of merit is most appropriate for a given application.en_US
dc.format.extent91100 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_USen_US
dc.publisherGeorgia Institute of Technologyen_US
dc.relation.ispartofseriesASDL;AIAA-2000-3715en_US
dc.subjectThermodynamic propertiesen_US
dc.subjectGas turbine enginesen_US
dc.subjectAircraft enginesen_US
dc.subjectFigure of meriten_US
dc.titleA Comparision of Thermodynamic Loss Models Applied to the J-79 Turbojet Engineen_US
dc.typePaper


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