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dc.contributor.authorAyaz, Süleyman Kagan
dc.contributor.authorAltuntaş, Önder
dc.date.accessioned2019-10-20T19:32:21Z
dc.date.available2019-10-20T19:32:21Z
dc.date.issued2017
dc.identifier.issn2050-0467
dc.identifier.issn2050-0475
dc.identifier.urihttps://dx.doi.org/10.1504/IJSA.2017.10011238
dc.identifier.urihttps://hdl.handle.net/11421/18441
dc.descriptionWOS: 000429596900004en_US
dc.description.abstractThe aim of this study is to determine optimum working of a generic ramjet engine. A thermodynamic analysis has been performed to evaluate three different ramjet flight conditions that have been obtained by using GasTurb. The results show that the entropy production in the diffusor (by the shocks) is of much importance as the combustor. The 2 Mach flight state has the highest fuel economy in compared to 3 and 4 Mach. 4 Mach creates the most irreversible process for given conditions. 4 Mach is the vulnerable one to pressure change since it has more thrust loss against pressure increase, which may happen during descend.en_US
dc.language.isoengen_US
dc.publisherInderscience Enterprises LTDen_US
dc.relation.isversionof10.1504/IJSA.2017.10011238en_US
dc.rightsinfo:eu-repo/semantics/closedAccessen_US
dc.subjectThermodynamic Analysisen_US
dc.subjectRamjet Engineen_US
dc.subjectThermodynamic Performance Evaluationen_US
dc.subjectThrusten_US
dc.subjectImpulseen_US
dc.titleAssessment of a ramjet engine for different Mach numbersen_US
dc.typearticleen_US
dc.relation.journalInternational Journal of Sustainable Aviationen_US
dc.contributor.departmentAnadolu Üniversitesi, Havacılık ve Uzay Bilimleri Fakültesien_US
dc.identifier.volume3en_US
dc.identifier.issue4en_US
dc.identifier.startpage325en_US
dc.identifier.endpage340en_US
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanıen_US]
dc.contributor.institutionauthorAltuntaş, Önder


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