Drag estimation on wedge-shaped protuberances in high-speed flows

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dc.contributor.authorKshitij, Abhinav
dc.contributor.authorPrince, Simon A.
dc.contributor.authorStollery, John L.
dc.date.accessioned2020-02-10T09:46:42Z
dc.date.available2020-02-10T09:46:42Z
dc.date.issued2020-01-05
dc.description.abstractA semi-empirical method is developed to estimate drag on wedge-shaped projections in hypersonic flow. Force balance measurements from gun tunnel tests directly measure total drag on blunt wedges, where the boundary layer and the entropy layer are weakly coupled. Detailed flowfield analysis from numerical simulations provides estimated locations of peak pressure ratio and skin friction. Schlieren images are used for detecting incipient separation in incoming flows with laminar and turbulent boundary layers. Test results indicate the presence of local hotspots at reattachment points of strong detached shocks on the wedge compression ramp, and of primary and secondary vortical structures around lateral faces. Total drag is found to decrease with decreasing bluntness but increasing slenderness in wedges tend to increase skin friction drag.en_UK
dc.identifier.citationKshitij A, Prince SA, Stollery JL. (2020) Drag estimation on wedge-shaped protuberances in high-speed flows. In: 2020 AIAA SciTech Forum, 6-10 January 2020, Orlando, Florida, USAen_UK
dc.identifier.isbn978-1-62410-595-1
dc.identifier.urihttps://doi.org/10.2514/6.2020-2053
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/15113
dc.language.isoenen_UK
dc.publisherAIAAen_UK
dc.relation.ispartofseries;AIAA 2020-2053
dc.rightsAttribution-NonCommercial 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc/4.0/*
dc.titleDrag estimation on wedge-shaped protuberances in high-speed flowsen_UK
dc.typeConference paperen_UK

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