Experimental and numerical studies of shock wave -- boundary-layer interactions over a cone-cylinder-flare in hypersonic flows

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dc.contributor.authorArfi, Benjamin W.
dc.contributor.authorCorcoral, Erwan A.
dc.contributor.authorPrince, Simon A.
dc.contributor.authorRana, Zeeshan A.
dc.contributor.authorTsentis, Spyros
dc.date.accessioned2025-02-26T16:00:45Z
dc.date.available2025-02-26T16:00:45Z
dc.date.freetoread2025-02-26
dc.date.issued2025-01-06
dc.date.pubOnline2025-01-03
dc.description.abstractThe present study provides experimental and numerical results for turbulent shockwave boundary layer interactions (SBLIs) over a blunt cone-cylinder-flare geometry, on which there is a lack of available data. Experiments were conducted in the Cranfield hypersonic gun tunnel, at Mach 8.2. Two configurations with varying nose length were studied using experimental testing and computational fluid dynamics (CFD). Three dimensionality has been generated by placing the model at incidence. The objective was to extend the range of data available for hypersonic flows and contribute to the design of re-entry vehicles. Experimental results cover forces and moments, that the numerical study aimed to replicate with Reynolds Averaged Navier-Stokes (RANS) modeling, and extended by analyzing the separated flow regions over the model. Additionally, the effect of the nose length on the aerodynamic forces and boundary layer transition were presented.
dc.description.conferencenameAIAA SCITECH 2025 Forum
dc.identifier.citationArfi BW, Corcoral EA, Prince SA, et al., (2025) Experimental and numerical studies of shock wave -- boundary-layer interactions over a cone-cylinder-flare in hypersonic flows. In: AIAA SCITECH 2025 Forum, 6-10 Jan 2025, Orlando FL, USA. Paper number AIAA 2025-1333
dc.identifier.elementsID564018
dc.identifier.paperNoAIAA 2025-1333
dc.identifier.urihttps://doi.org/10.2514/6.2025-1333
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23523
dc.language.isoen
dc.publisherAIAA
dc.publisher.urihttps://arc.aiaa.org/doi/10.2514/6.2025-1333
dc.rightsAttribution 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/
dc.subjecthypersonic flows
dc.subjectshock wave boundary layer interactions
dc.subject4015 Maritime Engineering
dc.subject40 Engineering
dc.subject4001 Aerospace Engineering
dc.subject51 Physical Sciences
dc.titleExperimental and numerical studies of shock wave -- boundary-layer interactions over a cone-cylinder-flare in hypersonic flows
dc.typeConference paper
dcterms.coverageOrlando, FL
dcterms.dateAccepted2024-08-31
dcterms.temporal.endDate10 Jan 2025
dcterms.temporal.startDate6 Jan 2025

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