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dc.contributor.advisorBrophy, Christopher M.
dc.contributor.authorHutcheson, Patrick D.
dc.date.accessioned2012-03-14T17:35:12Z
dc.date.available2012-03-14T17:35:12Z
dc.date.issued2006-12
dc.identifier.urihttp://hdl.handle.net/10945/2445
dc.description.abstractry at simulated flight conditions, including supersonic cruising conditions. The spiral lines initiator demonstrated a lower total pressure loss with compared to the geometry with rings, and thus was the preferred initiator configuraiton. Experimental values for the turbulence were found to be significantly lower than the computed values at similar conditions when using the k-e model. Finally, successful ignitions of the JP-10/Air initiator at frequencies of up to 20 Hz were experimentally demonstrated.en_US
dc.description.urihttp://archive.org/details/designmodelingnd109452445
dc.format.extentxvi, 99 p. : ill. ;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. Copyright protection is not available for this work in the United States.en_US
dc.subject.lcshComputational fluid dynamicsen_US
dc.subject.lcshMechanical engineeringen_US
dc.titleDesign, modeling and performance of a split path JP-10/Air Pulse Detonation engineen_US
dc.typeThesisen_US
dc.contributor.secondreaderHobson, Garth V.
dc.contributor.corporateNaval Postgraduate School (U.S.).
dc.contributor.departmentMechanical and Aerospace Engineering (MAE)
dc.description.funderFunded by: N0001406WR20161.en_US
dc.identifier.oclc80985844
etd.thesisdegree.nameM.S.en_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineMechanical Engineering and Mechanical Engineeren_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
etd.verifiednoen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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