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Aerodynamic Analysis Of A Vertically Landing Lifting Body

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dc.contributor.author Aradağ, Selin
dc.contributor.author Seidel, Jurgen
dc.contributor.author Cummings, Russell M.
dc.contributor.author Cook, Layne
dc.date.accessioned 2019-06-26T08:07:04Z
dc.date.available 2019-06-26T08:07:04Z
dc.date.issued 2015
dc.identifier.citation Aradag, 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.issn 1300-3615
dc.identifier.uri https://doi.org/10.2514/6.2007-4477
dc.identifier.uri http://hdl.handle.net/20.500.11851/1516
dc.description.abstract The 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.sponsorship This 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.iso eng en_US
dc.publisher Turkish Soc Thermal Sciences Technology en_US
dc.rights info:eu-repo/semantics/closedAccess
dc.subject computational fluid dynamics en_US
dc.subject vertical landing en_US
dc.subject aerodynamics en_US
dc.subject flow control en_US
dc.subject blowing en_US
dc.title Aerodynamic Analysis Of A Vertically Landing Lifting Body en_US
dc.type article en_US
dc.relation.journal Journal Of Thermal Science And Technology en_US
dc.relation.journal Isı Bilimi ve Tekniği Dergisi tr_TR
dc.contributor.department TOBB ETU, Faculty of Engineering, Department of Mechanical Engineering en_US
dc.contributor.department TOBB ETÜ, Mühendislik Fakültesi, Makine Mühendisliği Bölümü tr_TR
dc.identifier.volume 35
dc.identifier.issue 1
dc.identifier.startpage 35
dc.identifier.endpage 42
dc.contributor.orcid http://orcid.org/0000-0002-2034-0008
dc.identifier.wos WOS:000353855200005
dc.identifier.scopus 2-s2.0-35648991319
dc.contributor.tobbetuauthor Aradağ, Selin
dc.contributor.YOKid 143685
dc.relation.publicationcategory Makale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanı tr_TR


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