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

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dc.contributor.author Kshitij, Abhinav
dc.contributor.author Prince, Simon A.
dc.contributor.author Stollery, John L.
dc.date.accessioned 2020-02-10T09:46:42Z
dc.date.available 2020-02-10T09:46:42Z
dc.date.issued 2020-01-05
dc.identifier.citation Kshitij 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, USA en_UK
dc.identifier.isbn 978-1-62410-595-1
dc.identifier.uri https://doi.org/10.2514/6.2020-2053
dc.identifier.uri http://dspace.lib.cranfield.ac.uk/handle/1826/15113
dc.description.abstract A 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.language.iso en en_UK
dc.publisher AIAA en_UK
dc.relation.ispartofseries ;AIAA 2020-2053
dc.rights Attribution-NonCommercial 4.0 International *
dc.rights.uri http://creativecommons.org/licenses/by-nc/4.0/ *
dc.title Drag estimation on wedge-shaped protuberances in high-speed flows en_UK
dc.type Conference paper en_UK

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