Gelişmiş Arama

Basit öğe kaydını göster

dc.contributor.authorCavcar, Mustafa
dc.contributor.authorCavcar, Aydan
dc.date.accessioned2019-10-18T18:44:07Z
dc.date.available2019-10-18T18:44:07Z
dc.date.issued2003
dc.identifier.issn0021-8669
dc.identifier.urihttps://dx.doi.org/10.2514/2.6879
dc.identifier.urihttps://hdl.handle.net/11421/10533
dc.descriptionWOS: 000185853300009en_US
dc.description.abstractTwo different approximate solutions are proposed and compared with the numerical solution of the constant-altitude-constant-Mach-number cruise range for turbojet/fan aircraft. The approximate solutions consider both cambered wing drag polar and dependence of specific fuel consumption on Mach number. It is also proved that the classical analytical approach assuming constant specific fuel consumption and uncambered wing drag polar results in higher optimum Mach numbers and shorter ranges for constant-altitude-constant-airspeed flight of turbojet/fan transport aircraft.en_US
dc.language.isoengen_US
dc.publisherAmer Inst Aeronaut Astronauten_US
dc.relation.isversionof10.2514/2.6879en_US
dc.rightsinfo:eu-repo/semantics/closedAccessen_US
dc.titleComparison of generalized approximate cruise range solutions for turbojet/fan aircraften_US
dc.typearticleen_US
dc.relation.journalJournal of Aircraften_US
dc.contributor.departmentAnadolu Üniversitesien_US
dc.identifier.volume40en_US
dc.identifier.issue5en_US
dc.identifier.startpage891en_US
dc.identifier.endpage895en_US
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanıen_US
dc.contributor.institutionauthorCavcar, Mustafa
dc.contributor.institutionauthorCavcar, Aydan


Bu öğenin dosyaları:

Thumbnail

Bu öğe aşağıdaki koleksiyon(lar)da görünmektedir.

Basit öğe kaydını göster