Aishwarya PS, Mohammed Ibrahim SUGARNO

DOI Number: 10.82241/ceas-hisst-2024-275

Conference number: HiSST-2024-275

The present work examines the shock-wave boundary layer interaction resulting from the impingement of an oblique shock wave, created by a 38-degree wedge, on a flat plate in a flow with a Mach number of six. The primary emphasis of the analysis is centered on the attainment of Mach reflection, wherein the Mach stem serves as a distinctive attribute for observing the Edney type II shock interaction occurring on the flat plate. Consequently, the establishment of a separation bubble, along with the accompanying phenomena of separation, reflected shock, and reattachment shock, occurs. The intensity of these phenomena varies depending on the vertical and streamwise distance at which the shock impinges on the flat plate. The experimental investigations in the Ludwieg tunnel and computational fluid dynamic analysis using the Ansys Fluent solver in laminar flow gives a comprehensive understanding of the flow. This research aimed to examine the two-dimensional implications of the observed occurrence.

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In Categories: 1.Events, HiSST 2024, Hypersonic Fundamentals and History
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