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dc.contributor.advisorBrophy, Christopher M.
dc.contributor.authorWittmers, Nicole K.
dc.dateDecember 2004
dc.date.accessioned2012-03-14T17:31:12Z
dc.date.available2012-03-14T17:31:12Z
dc.date.issued2004-12
dc.identifier.urihttp://hdl.handle.net/10945/1297
dc.descriptionApproved for public release, distribution is unlimiteden_US
dc.description.abstractOperational characteristics of a valveless pulse detonation engine system were characterized by experimental measurements of thrust, fuel flow, and internal gas dynamics. The multi-cycle detonation experiments were performed on an axis-symmetric engine geometry operating on an ethylene/air mixtures. The detonation diffraction process from a small 'initiator' combustor to a larger diameter main combustor in a continuous airflow configuration was evaluated during multi-cycle operation of a pulse detonation engine and was found to be very successful at initiating combustion of the secondary fuel/air mixture at high frequencies. The configuration was used to demonstrate the benefit of generating an overdriven detonation condition near the diffraction plane for enhanced transmission of the larger combustor. Results have shown that the addition of optical sensors, such as tunable diode lasers, to provide fuel profile data are invaluable for providing high fidelity performance results. The performance results demonstrated the ability of the valveless pulse detonation engine to run at efficiencies similar to valved pulse detonation engine geometries and may be a low cost alternative to conventional air-breathing propulsion systems.en_US
dc.format.extentxvi, 61 p. : ill. (chiefly col.)en_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. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted.en_US
dc.subject.lcshDetonation wavesen_US
dc.subject.lcshCombustionen_US
dc.subject.lcshAirplanesen_US
dc.subject.lcshMotorsen_US
dc.subject.lcshThrusten_US
dc.titleDirect-connect performance evaluation of a valveless pulse detonation engineen_US
dc.typeThesisen_US
dc.contributor.secondreaderHobson, Garth
dc.contributor.corporateNaval Postgraduate School (U.S.).
dc.contributor.departmentMechanical and Astronautical Engineering (MAE)
dc.subject.authorPulse detonation engineen_US
dc.subject.authorSupersonic air breathingen_US
dc.subject.authorEngine performance evaluationen_US
dc.description.funderFunded By: N00014OWR20226.en_US
dc.description.serviceLieutenant, United States Navyen_US
etd.thesisdegree.nameM.S. in Astronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAstronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
etd.verifiednoen_US


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