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dc.contributor.authorSpeakman, G. C.
dc.contributor.authorHayes, J. D.
dc.contributor.authorNetzer, D. W.
dc.date.accessioned2013-08-14T17:17:55Z
dc.date.available2013-08-14T17:17:55Z
dc.date.issued1976-12
dc.identifier.urihttp://hdl.handle.net/10945/35242
dc.descriptionReproduction of all or part of this report is authorized.en_US
dc.description.abstractElliptic computer codes have been developed (including plot routines) which can be used to study the flow field in test cells and exhaust stacks and in the augmenter tube for low thrust operation. The effects of engine-augmenter spacing, augmenter diameter and inlet design, aft cell wall location, test cell by-pass ratio, call inlet conditions and stack-augmenter geometry on the flow field and augmenter pressure rise have been calculated. The models appear to be qualitatively correct and adequate for their intended purposes but model validation with experiment is required.en_US
dc.description.sponsorshipThe work reported herein was supported by the Naval Air Propulsion Test Center, Trenton, New Jersey, and the Naval Environmental Protection Data Support Service.en_US
dc.language.isoen_US
dc.publisherMonterey, California: Naval Postgraduate School.en_US
dc.subjectTurbojet Test Cellen_US
dc.subjectAugmenteren_US
dc.subjectFlow Modelen_US
dc.titleInternal Aerodynamics of Turbojet Test Cellsen_US
dc.typeTechnical Reporten_US
dc.contributor.secondreaderBell, R. W.
dc.contributor.departmentAeronautics
dc.identifier.npsreportNPS-67Nt76121
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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