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dc.contributor.authorCerminara, Adriano
dc.contributor.authorDurant, Antoine
dc.contributor.authorAndré, Thierry
dc.contributor.authorSandham, Neil D
dc.contributor.authorTaylor, Nigel J
dc.date.accessioned2019-11-26T11:18:34Z
dc.date.available2019-11-26T11:18:34Z
dc.date.issued2018-11-12
dc.identifier.citationCerminara, Adriano, Durant, Antoine, André, Thierry, Sandham, Neil and Taylor, Nigel (2018) Receptivity to freestream acoustic noise in hypersonic flow over a generic forebody. Journal of Spacecraft and Rockets, 1-11. (doi:10.2514/1.A34283).en
dc.identifier.issn0022-4650en
dc.identifier.doi10.2514/1.a34283en
dc.identifier.urihttp://hdl.handle.net/2436/622938
dc.description.abstractDirect numerical simulations of the Navier–Stokes equations have been performed to investigate the receptivity and breakdown mechanisms in a Mach 6 flow over a generic forebody geometry with freestream acoustic disturbances. The simulations are based on transition experiments carried out in April 2015 in the Boeing/U.S. Air Force Office of Scientific Research Mach 6 facility at Purdue University. A three-dimensional model for both fast and slow freestream acoustic waves with multiple frequencies and spanwise wave numbers has been adopted in the numerical simulations, for which high-amplitude disturbances have been considered in order to simulate noisy wind-tunnel conditions. The numerical results revealed similarities in comparison to the experimental observations, especially when slow acoustic waves were considered as freestream disturbances. In particular, slow acoustic waves have been found to induce the breakdown process via crossflow instabilities located in the off-centerline region, with formation of streamwise streaks. Fast acoustic waves, in contrast, appeared more efficient in inducing earlier nonlinear growth through destabilization of the boundary layer along the symmetry plane of the body.en
dc.formatapplication/pdfen
dc.languageen
dc.language.isoenen
dc.publisherAmerican Institute of Aeronautics and Astronautics (AIAA)en
dc.relation.urlhttps://arc.aiaa.org/doi/10.2514/1.A34283en
dc.subjecthypersonicsen
dc.subjectnumerical simulationen
dc.subjectboundary layer receptivityen
dc.subjecttransitionen
dc.subjectacoustic wavesen
dc.titleReceptivity to freestream acoustic noise in hypersonic flow over a generic forebodyen
dc.typeJournal articleen
dc.identifier.eissn1533-6794
dc.identifier.journalJournal of Spacecraft and Rocketsen
dc.date.updated2019-11-22T14:47:44Z
dc.date.accepted2018-08-10
rioxxterms.funderUniversity of Southampton
rioxxterms.identifier.projectUOW26112019ACen
rioxxterms.versionAMen
rioxxterms.licenseref.urihttps://creativecommons.org/licenses/by-nc/4.0/en
rioxxterms.licenseref.startdate2019-11-26en
dc.source.volume56
dc.source.issue2
dc.source.beginpage447
dc.source.endpage457
dc.description.versionPublished version
refterms.dateFCD2019-11-26T11:18:24Z
refterms.versionFCDAM
refterms.dateFOA2019-11-26T11:18:34Z


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