Flow Diagnostics in Shock Wave-Boundary Layer Interaction Experiments in Hypersonic Flow

Mohd Rashdan Saad; Azam Che Idris; Konstantinos Kontis

doi:10.4028/www.scientific.net/AMM.660.669

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 660Flow Diagnostics in Shock Wave-Boundary Layer...

Flow Diagnostics in Shock Wave-Boundary Layer Interaction Experiments in Hypersonic Flow

Abstract:

Shock Wave-Boundary Layer Interaction (SBLI) is a phenomenon occurring in high-speed propulsion systems that is highly undesirable. Numerous methods have been tested to manipulate and control SBLI which includes both active and passive flow control techniques. To determine the improvements brought by the flow control techniques, advanced and state-of the-art flow diagnostics and experimental techniques are required, especially when it involves high-speed flows. In this study, a number of advanced flow diagnostics were employed to investigate the effect of micro-vortex generators in controlling SBLI in Mach 5 such as Pressure Sensitive Paints (PSP), Particle Image Velocimetry (PIV), schlieren photography and oil-flow visualization. The flow diagnostics successfully visualized the boundary layer separation and also the improvements brought by the micro-vortex generators.

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Periodical:

Applied Mechanics and Materials (Volume 660)

Pages:

669-673

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.660.669

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Online since:

October 2014

Authors:

Mohd Rashdan Saad*, Azam Che Idris, Konstantinos Kontis

Keywords:

Flow Diagnostic, Hypersonic, PIV, Pressure Sensitive Paint, Shock Wave

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