DC Field | Value | Language |
---|---|---|
dc.contributor.author | Lee, S. | ko |
dc.contributor.author | Loth, E. | ko |
dc.date.accessioned | 2020-03-19T02:25:28Z | - |
dc.date.available | 2020-03-19T02:25:28Z | - |
dc.date.created | 2020-02-17 | - |
dc.date.created | 2020-02-17 | - |
dc.date.created | 2020-02-17 | - |
dc.date.issued | 2018-10 | - |
dc.identifier.citation | AERONAUTICAL JOURNAL, v.122, no.1256, pp.1568 - 1585 | - |
dc.identifier.issn | 0001-9240 | - |
dc.identifier.uri | http://hdl.handle.net/10203/272666 | - |
dc.description.abstract | A 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.language | English | - |
dc.publisher | CAMBRIDGE UNIV PRESS | - |
dc.title | On ramped vanes to control normal shock boundary layer interactions | - |
dc.type | Article | - |
dc.identifier.wosid | 000447251800004 | - |
dc.identifier.scopusid | 2-s2.0-85054920831 | - |
dc.type.rims | ART | - |
dc.citation.volume | 122 | - |
dc.citation.issue | 1256 | - |
dc.citation.beginningpage | 1568 | - |
dc.citation.endingpage | 1585 | - |
dc.citation.publicationname | AERONAUTICAL JOURNAL | - |
dc.identifier.doi | 10.1017/aer.2018.88 | - |
dc.contributor.localauthor | Lee, S. | - |
dc.contributor.nonIdAuthor | Loth, E. | - |
dc.description.isOpenAccess | N | - |
dc.type.journalArticle | Article | - |
dc.subject.keywordAuthor | Shock-induced Flow Separation | - |
dc.subject.keywordAuthor | Flow Control | - |
dc.subject.keywordAuthor | Vortex Generators | - |
dc.subject.keywordPlus | LARGE-EDDY SIMULATION | - |
dc.subject.keywordPlus | DIRECT NUMERICAL-SIMULATION | - |
dc.subject.keywordPlus | VORTEX GENERATORS | - |
dc.subject.keywordPlus | COMPRESSION-RAMP | - |
dc.subject.keywordPlus | SEPARATION | - |
dc.subject.keywordPlus | MICRORAMPS | - |
dc.subject.keywordPlus | FLOWS | - |
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