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dc.contributor.advisorHobson, Garth V.
dc.contributor.authorAndreou, Loukas.
dc.dateSeptember, 1999
dc.date.accessioned2012-09-07T15:35:17Z
dc.date.available2012-09-07T15:35:17Z
dc.date.issued1999-09
dc.identifier.urihttp://hdl.handle.net/10945/13655
dc.description.abstractA turbo-ramjet engine configuration has possible applications in missiles or Uninhabited Aerial Vehicle's (UAV's). In order to study possible configurations, a Sophia J450 turbojet engine was used, with varying shroud configurations, to compare static thrust and specific fuel consumption measured in a test rig. A baseline shroud, which covered the engine, was tested with three ducts lengths aft of the J450's exhaust. Bach duct length was tested with and without the final convergent nozzle. An elliptic intake for the shroud was also manufactured and tested on two of the configurations. Shroud pressures were also recorded to determine the amount of entrainment of secondary flow into the shroud. The short shroud was found to produce the best performance of the three configurations tested.en_US
dc.description.urihttp://archive.org/details/performanceofduc1094513655
dc.format.extentx, 81 p.;28 cm.en_US
dc.language.isoen_US
dc.publisherMonterey, California: Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.en_US
dc.titlePerformance of a ducted micro-turbojet engineen_US
dc.typeThesisen_US
dc.description.serviceHellenic Navy author.en_US
etd.thesisdegree.nameM.S. in Aeronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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