The interaction between a sonic jet and an oblique shock wave in a supersonic crossflow

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The current study considers the configuration of a transverse jet in a supersonic crossflow that is interacting with an impinging oblique shock wave. The relevance of this configuration is associated to high-speed air-breathing propulsion systems, where a shock may be induced in the combustion chamber to enhance mixing. To investigate the behaviour of this system, experiments were conducted in a supersonic test facility at a freestream Mach number of 2, analyzing the effect of three main control variables: the jet momentum flux ratio, the shock strength and the impingement position of the shock on the jet plume. Measurements were acquired using surface oil-flow visualization, schlieren photography and Particle Image Velocimetry. Results reveal that near-field momentum-driven mixing remains largely unaffected after the introduction of the impinging shock wave, while mid-to-far-field mixing mechanisms do change. An increase in jet plume elevation was observed, as well as the formation of a strong shear layer downstream of the jet, which acts as a source of vorticity that promotes entrainment towards the jet mid-field. A stronger shock wave was found to be more beneficial for mixing performance. This effect was seen to decrease with weakening shock strength or by shifting the strong shock further downstream.
Original languageEnglish
Title of host publicationAIAA SCITECH 2022 Forum
Number of pages15
ISBN (Electronic) 978-1-62410-631-6
Publication statusPublished - 2022
EventAIAA SCITECH 2022 Forum - virtual event
Duration: 3 Jan 20227 Jan 2022

Publication series

NameAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022


ConferenceAIAA SCITECH 2022 Forum


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