In this work, separation due to the interaction of normal shock with wall boundary layers in a supersonic duct flow is studied using schlieren, oil flow visualization, and pressure measurements. This study uses separation control devices on three walls of a rectangular duct and investigates the influence of adding control on one wall and on the other walls. It was found that control on any wall has effect on separation on other walls. This effect was found to be due to the change in the size of corner separations. Pressure recovery was found to be steeper with the introduction of more control devices in the duct. © IMechE 2018.

Thiruchengode M. Muruganandam

Department of Aerospace Engineering

S. Vaisakh

Boundary layers

Shock waves

BOUNDARY LAYER INTERACTION

Boundary-layer separation

MICRO VORTEX

OIL FLOW VISUALIZATION

RECTANGULAR DUCTS

Separation control

SHOCK INDUCED SEPARATION

SUPERSONIC DUCT

Ducts

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IIT Madras

Influence of multi-wall separation control on normal-shock-induced separation in supersonic duct flows:

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

Experiments have been conducted in a supersonic rectangular duct (Mach 1.4), with a normal shock wave/boundary layer interaction. The duct is designed in a modular fashion so that its aspect ratio can be varied without a change in the flow geometry. The shock location, duct height, and Mach number are kept constant, while varying the aspect ratio. Conventional and inclined schlieren techniques have been used to visualize the normal shock. The height and width of the “normal part” of the normal shock have been measured. A parameter termed area fraction of the normal shock is used to quantify the extent of shock bifurcation, and the effect of the duct aspect ratio on this parameter is studied. It has been found that a nearly square duct is the preferred geometry for maximizing the area fraction of the normal shock. © 2019, Springer-Verlag GmbH Germany, part of Springer Nature.

Shock Waves

Effect of duct aspect ratio on normal shock wave/boundary layer interaction

Influence of multi-wall separation control on normal-shock-induced separation in supersonic duct flows

Journal	Data powered by TypesetProceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
Publisher	Data powered by TypesetSAGE Publications Ltd
ISSN	09544100
Open Access	No