Please use this identifier to cite or link to this item:
http://hdl.handle.net/10397/93821
DC Field | Value | Language |
---|---|---|
dc.contributor | Department of Aeronautical and Aviation Engineering | en_US |
dc.creator | Zhang, Z | en_US |
dc.creator | Liu, Y | en_US |
dc.creator | Wen, C | en_US |
dc.date.accessioned | 2022-08-01T06:00:20Z | - |
dc.date.available | 2022-08-01T06:00:20Z | - |
dc.identifier.issn | 0022-1120 | en_US |
dc.identifier.uri | http://hdl.handle.net/10397/93821 | - |
dc.language.iso | en | en_US |
dc.publisher | Cambridge University Press | en_US |
dc.rights | © The Author(s), 2022. Published by Cambridge University Press. This is an Open Access article, distributed under the terms of the Creative Commons Attribution licence (https://creativecommons. org/licenses/by/4.0/), which permits unrestricted re-use, distribution, and reproduction in any medium, provided the original work is properly cited. | en_US |
dc.rights | The following publication Zhang, Z., Liu, Y., & Wen, C. (2022). Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner. Journal of Fluid Mechanics, 940, A29 is available at https://doi.org/10.1017/jfm.2022.226. | en_US |
dc.subject | Detonation waves | en_US |
dc.title | Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner | en_US |
dc.type | Journal/Magazine Article | en_US |
dc.identifier.volume | 940 | en_US |
dc.identifier.doi | 10.1017/jfm.2022.226 | en_US |
dcterms.abstract | The stabilization of oblique detonation waves (ODWs) in an engine combustor is important for the successful applications of oblique detonation engines, and comprehensively understanding the effects of the inviscid reflection of ODWs on their stabilization and the relevant mechanisms is imperative to overall combustor design. In this study, the flow fields of ODW reflections in a space-confined combustor are numerically studied by solving the two-dimensional time-dependent multispecies Euler equations in combination with a detailed hydrogen combustion mechanism. The inviscid Mach reflections of ODWs before an expansion corner are emphasized with different flight Mach numbers, Ma, and different dimensionless reflection locations, ζ ≥ 0 (ζ = 0: the ODW reflects precisely at the expansion corner; ζ > 0: the ODW reflects off the wall before the expansion corner). Two kinds of destabilization phenomena of the inviscid Mach reflection of an ODW induced by different mechanisms are found, namely wave-induced destabilization at large ζ > 0 for moderate (not very low) Ma and inherent destabilization at any ζ > 0 for low Ma. Wave-induced destabilization is attributed to the incompatibility between the pressure ratio across the Mach stem and its relative propagation speed, which is triggered by the action of the secondary reflected shock wave or the transmitted Mach stem on the subsonic zone behind the Mach stem. Inherent destabilization is demonstrated through an in-depth theoretical analysis and is attributed to geometric choking of the flow behind the Mach stem. | en_US |
dcterms.accessRights | open access | en_US |
dcterms.bibliographicCitation | Journal of fluid mechanics, 10 June 2022, v. 940, A29 | en_US |
dcterms.isPartOf | Journal of fluid mechanics | en_US |
dcterms.issued | 2022-06-10 | - |
dc.identifier.scopus | 2-s2.0-85128822986 | - |
dc.identifier.eissn | 1469-7645 | en_US |
dc.identifier.artn | A29 | en_US |
dc.description.validate | 202208_bcww | en_US |
dc.description.oa | Version of Record | en_US |
dc.identifier.FolderNumber | OA_TA | - |
dc.description.pubStatus | Published | en_US |
dc.description.TA | CUP (2021) | en_US |
dc.description.oaCategory | TA | en_US |
Appears in Collections: | Journal/Magazine Article |
Files in This Item:
File | Description | Size | Format | |
---|---|---|---|---|
Zhang_Mechanisms_Destabilized_Mach.pdf | 3.63 MB | Adobe PDF | View/Open |
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