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dc.contributor.advisorBrophy, Christopher
dc.contributor.authorJohnson, Robert G.
dc.date.accessioned2012-08-09T18:47:25Z
dc.date.available2012-08-09T18:47:25Z
dc.date.issued2000-06-01
dc.identifier.urihttp://hdl.handle.net/10945/7664
dc.description.abstractCurrent interest in developing a low cost, less complex tactical missile propulsion system that operates on readily available liquid fuels and can operate from low subsonic to a flight Mach number of 5 is driving research on pulse detonation engines. This research program involved the design, construction, and testing of a valveless Pulse Detonation Engine using a JP-10/ air mixture as the primary combustible reactants. A small JP-10/oxygen pre- detonation tube was used to initiate the detonation in the JP-10/air mixture in the engine. The engine was tested at various inlet conditions and equivalence ratios in order to determine the detonable regime of the fuel/air mixture. The original area transition from the pre-detonation tube to the main combustion tube appeared to be too extreme, so a tube was added to extend the pre- detonation tube into the throat of a shock focusing device inserted flush with the head end of the main combustion tube to promote more favorable transition conditionsen_US
dc.description.urihttp://www.archive.org/details/designcharacteri00john
dc.format.extentxiv, 106 p.;28 cm.en_US
dc.language.isoen_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.titleDesign, characterization, and performance of a valveless pulse detonation engineen_US
dc.typeThesisen_US
dc.description.serviceU.S. Navy (U.S.N.) author.en_US
dc.identifier.oclcocn640945865
etd.thesisdegree.nameM.S. in Astronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAstronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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