On ramped vanes to control normal shock boundary layer interactions

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dc.contributor.authorLee, S.ko
dc.contributor.authorLoth, E.ko
dc.date.accessioned2020-03-19T02:25:28Z-
dc.date.available2020-03-19T02:25:28Z-
dc.date.created2020-02-17-
dc.date.created2020-02-17-
dc.date.created2020-02-17-
dc.date.issued2018-10-
dc.identifier.citationAERONAUTICAL JOURNAL, v.122, no.1256, pp.1568 - 1585-
dc.identifier.issn0001-9240-
dc.identifier.urihttp://hdl.handle.net/10203/272666-
dc.description.abstractA novel vortex generator design positioned upstream of a normal shock followed by a subsequent diffuser was investigated using large eddy simulations. In particular, ""ramped-vane"" flow control devices with three different heights relative to the incoming boundary layer thickness (0.34 delta, 0.52 delta and 0.75 delta) were placed in a supersonic boundary layer with a freestream Mach number of 1.3 and a Reynolds number of 2400 based on the momentum thickness. This is the first numerical study to investigate the size effect of the ramped-vane for flow control device in terms of shape factor, flow separation and flow unsteadiness. The results showed that these devices generated strong streamwise vortices that entrained high-momentum fluid to the near-wall region and increased turbulent mixing. The devices also decreased shock-induced flow separation, which resulted in a higher downstream skin friction in the diffuser. In general, the largest ramped-vane (0.75 delta) produced the largest reductions in flow separation, shape factor and overall unsteadiness. These results and a careful review of the literature study also determined the quantitative correlation of optimum VG height with Mach number, whereby h/delta similar to 1 is often optimum for incompressible flows while higher Mach numbers lead to small optimum heights, tending towards h/delta similar to 0.45 at M = 2.5.-
dc.languageEnglish-
dc.publisherCAMBRIDGE UNIV PRESS-
dc.titleOn ramped vanes to control normal shock boundary layer interactions-
dc.typeArticle-
dc.identifier.wosid000447251800004-
dc.identifier.scopusid2-s2.0-85054920831-
dc.type.rimsART-
dc.citation.volume122-
dc.citation.issue1256-
dc.citation.beginningpage1568-
dc.citation.endingpage1585-
dc.citation.publicationnameAERONAUTICAL JOURNAL-
dc.identifier.doi10.1017/aer.2018.88-
dc.contributor.localauthorLee, S.-
dc.contributor.nonIdAuthorLoth, E.-
dc.description.isOpenAccessN-
dc.type.journalArticleArticle-
dc.subject.keywordAuthorShock-induced Flow Separation-
dc.subject.keywordAuthorFlow Control-
dc.subject.keywordAuthorVortex Generators-
dc.subject.keywordPlusLARGE-EDDY SIMULATION-
dc.subject.keywordPlusDIRECT NUMERICAL-SIMULATION-
dc.subject.keywordPlusVORTEX GENERATORS-
dc.subject.keywordPlusCOMPRESSION-RAMP-
dc.subject.keywordPlusSEPARATION-
dc.subject.keywordPlusMICRORAMPS-
dc.subject.keywordPlusFLOWS-
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