Please use this identifier to cite or link to this item:
http://hdl.handle.net/10397/88402
DC Field | Value | Language |
---|---|---|
dc.contributor | Department of Mechanical Engineering | - |
dc.creator | Hao, J | - |
dc.creator | Wen, CY | - |
dc.date.accessioned | 2020-11-03T09:00:56Z | - |
dc.date.available | 2020-11-03T09:00:56Z | - |
dc.identifier.issn | 0022-1120 | - |
dc.identifier.uri | http://hdl.handle.net/10397/88402 | - |
dc.language.iso | en | en_US |
dc.publisher | Cambridge University Press | en_US |
dc.rights | This article has been published in a revised form in Journal of Fluid Mechanics https://dx.doi.org/10.1017/jfm.2020.331. This version is free to view and download for private research and study only. Not for re-distribution or re-use. © The Author(s), 2020. | - |
dc.rights | When citing an Accepted Manuscript or an earlier version of an article, the Cambridge University Press requests that readers also cite the Version of Record with a DOI link. The article is subsequently published in revised form in Journal of Fluid Mechanics https://dx.doi.org/10.1017/jfm.2020.331. | - |
dc.subject | Boundary layer separation | en_US |
dc.subject | High-speed flow | en_US |
dc.subject | Shock waves | en_US |
dc.title | Hypersonic flow over spherically blunted double cones | en_US |
dc.type | Journal/Magazine Article | en_US |
dc.identifier.spage | A26-1 | - |
dc.identifier.epage | A26-21 | - |
dc.identifier.volume | 896 | - |
dc.identifier.doi | 10.1017/jfm.2020.331 | - |
dcterms.abstract | A hypersonic shock wave/laminar boundary-layer interaction over a canonical double-cone configuration is numerically investigated. A moderate-enthalpy flow of with a Mach number of 9.87 and a unit Reynolds number of is considered. Special emphasis is given to the influence of leading-edge bluntness. The results indicate that the double-cone flow is insensitive to small bluntness in terms of shock structures, separation region sizes and surface pressure and heat flux distributions. A critical nose radius is observed, beyond which the separation bubble grows dramatically. The numerical data are analysed and interpreted based on a triple-deck formulation. It is shown that the sudden change in flow features is mainly caused by pressure overexpansion on the first cone due to leading-edge bluntness, such that the skin friction upstream of the separation is significantly reduced and the upstream pressure can no longer resist the large adverse pressure gradient induced by shock impingement. An estimation of the critical radius is established based on the pressure correlations of Blick & Francis (AIAA J., vol. 4 (3), 1966, pp. 547-549) for spherically blunted cones. Simulations at a higher enthalpy with the presence of both vibrational relaxation and air chemistry show a similar trend with increasing nose radius. The proposed criterion agrees well with the experimental observations. | - |
dcterms.accessRights | open access | en_US |
dcterms.bibliographicCitation | Journal of fluid mechanics, 10 Aug. 2020, v. 896, A26, p. A26-1-A26-21 | - |
dcterms.isPartOf | Journal of fluid mechanics | - |
dcterms.issued | 2020 | - |
dc.identifier.scopus | 2-s2.0-85086265589 | - |
dc.identifier.eissn | 1469-7645 | - |
dc.identifier.artn | A26 | - |
dc.description.validate | 202011 bcrc | - |
dc.description.oa | Accepted Manuscript | en_US |
dc.identifier.FolderNumber | a0497-n01 | en_US |
dc.description.pubStatus | Published | en_US |
Appears in Collections: | Journal/Magazine Article |
Files in This Item:
File | Description | Size | Format | |
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Hypersonic_flow_over_spherically_blunted_double_cones.pdf | Pre-Published_version | 1.59 MB | Adobe PDF | View/Open |
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