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dc.contributor.authorNetzer, David W.
dc.date1972-01
dc.date.accessioned2013-04-29T23:27:48Z
dc.date.available2013-04-29T23:27:48Z
dc.date.issued1972-01
dc.identifier.urihttp://hdl.handle.net/10945/31782
dc.descriptionALL DISTRIBUTION OF THIS DOCUMENT IS CONTROLLED. REPRODUCTION AND DISTRIBUTION NOT AUTHORIZED. COPIES AVAILABLE ONLY FROM CPIA.en_US
dc.description.sponsorshipPrepared by CPIAen_US
dc.description.urihttp://archive.org/details/hybridrocketinte69netz
dc.language.isoen_US
dc.publisherLaurel, MD: Chemical Propulsion Information Agencyen_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.lcshHYBRID ROCKET ENGINES, MATHEMATICAL MODELS, REACTION KINETICS, REGRESSION ANALYSIS, COMBUSTION, CONVECTION(HEAT TRANSFER), INJECTORS, ENTHALPY, LIQUID ROCKET PROPELLANTS, SPECIFIC IMPULSE, THERMAL RADIATION, SOLID ROCKET PROPELLANTS, INTERIOR BALLISTICSen_US
dc.titleHybrid Rocket Internal Ballisticsen_US
dc.typeTechnical Reporten_US
dc.contributor.corporateNaval Postgraduate School
dc.identifier.npsreportCPIA Publication 222


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