Please use this identifier to cite or link to this item: https://hdl.handle.net/20.500.11851/1516
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dc.contributor.authorAradağ, Selin-
dc.contributor.authorSeidel, Jurgen-
dc.contributor.authorCummings, Russell M.-
dc.contributor.authorCook, Layne-
dc.date.accessioned2019-06-26T08:07:04Z
dc.date.available2019-06-26T08:07:04Z
dc.date.issued2015
dc.identifier.citationAradag, S., Seidel, J., Cummings, R., & Cook, L. (2007). Aerodynamic Analysis of a Vertically Landing Lifting Body. In 18th AIAA Computational Fluid Dynamics Conference (p. 4477).en_US
dc.identifier.issn1300-3615
dc.identifier.urihttps://doi.org/10.2514/6.2007-4477-
dc.identifier.urihttps://hdl.handle.net/20.500.11851/1516-
dc.description.abstractThe vertical landing lifting body (VLLB) is a new concept for reusable launch vehicles, which launches vertically, but re-enters the atmosphere at a high angle of attack (alpha) for its entire flight. The VLLB remains at high angles of attack through all Mach numbers under aerodynamic control until shortly before touchdown. One of the important risk areas for the VLLB concept concerns flight below Mach 2 at high angles of attack where the flow is dominated by separated, highly vortical behavior. The purpose of this study is to investigate the aerodynamic characteristics and control effectiveness of the high-alpha flow of the Hot Eagle Vertically Landing Lifting Body geometry. Several test cases were performed utilizing Detached Eddy Simulations (DES) to both analyze and control the flow over Hot Eagle geometry at different flow conditions. According to results of the time-dependent DES computations, the flow is symmetric and steady at both subsonic and transonic Mach numbers for both 45 and 60 degrees angle of attack. As the angle of attack or the Mach number increases, the vortices get stronger; but the flow remains steady and symmetric. This is probably because of the blunt nature of the nose and its cross-section. Symmetric and asymmetric blowing were performed to control the flow structure around the body. Different blowing rates have been investigated, and the vehicle is found to be controllable with reasonable amounts of blowing.en_US
dc.description.sponsorshipThis research was supported by Universal Space Lines LLC, monitored by Mike Talbot and Mike Mahoney. Funding for the work came from AFRL under the sponsorship of Jess Sponable. The authors would also like to thank to Dr. Dave McDaniel for his help in creating the grid for asymmetric blowing. The results of this study were presented at an AIAA conference.
dc.language.isoenen_US
dc.publisherTurkish Soc Thermal Sciences Technologyen_US
dc.relation.ispartofJournal Of Thermal Science And Technologyen_US
dc.relation.ispartofIsı Bilimi ve Tekniği Dergisien_US
dc.rightsinfo:eu-repo/semantics/closedAccessen_US
dc.subjectcomputational fluid dynamicsen_US
dc.subjectvertical landingen_US
dc.subjectaerodynamicsen_US
dc.subjectflow controlen_US
dc.subjectblowingen_US
dc.titleAerodynamic Analysis of a Vertically Landing Lifting Bodyen_US
dc.typeArticleen_US
dc.departmentFaculties, Faculty of Engineering, Department of Mechanical Engineeringen_US
dc.departmentFakülteler, Mühendislik Fakültesi, Makine Mühendisliği Bölümütr_TR
dc.identifier.volume35
dc.identifier.issue1
dc.identifier.startpage35
dc.identifier.endpage42
dc.authorid0000-0002-2034-0008-
dc.identifier.wosWOS:000353855200005en_US
dc.identifier.scopus2-s2.0-35648991319en_US
dc.institutionauthorAradağ, Selin-
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanıen_US
dc.identifier.scopusqualityQ2-
item.openairetypeArticle-
item.languageiso639-1en-
item.grantfulltextnone-
item.fulltextNo Fulltext-
item.openairecristypehttp://purl.org/coar/resource_type/c_18cf-
item.cerifentitytypePublications-
Appears in Collections:Makine Mühendisliği Bölümü / Department of Mechanical Engineering
Scopus İndeksli Yayınlar Koleksiyonu / Scopus Indexed Publications Collection
WoS İndeksli Yayınlar Koleksiyonu / WoS Indexed Publications Collection
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