Shock-wave boundary-layer interaction study on a compression corner using pressure-sensitive paint

Manisankar, C and Verma, SB and Raju, Channa (2012) Shock-wave boundary-layer interaction study on a compression corner using pressure-sensitive paint. International Journal of Aerospace Innovations, 4 (1-2). pp. 29-39. ISSN 1757-2258

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Abstract

Experiments have been performed to study a compression corner induced turbulent boundary layer interactions in a freestream Mach number of 2.05 without and with control. Two configurations of vortex generators (VG), in the form of an array of delta ramps placed upstream of the interaction region at 27.5δ or h/δ = 0.65, have been tested to control the interaction. Pressure sensitive paint (PSP) measurements were made using a binary paint developed in-house. Reasonably good agreement of PSP results with mean static pressure measurements has been observed. The spanwise wall pressure distribution immediately downstream of the control devices show a sinusoidal pattern indicating the generation of streamwise vortices from VG devices. The interaction of these vortices with the reverse flow in the separated region replaced a well-defined separation line for no control by a highly corrugated separation line. Relative to the no-control case, the peak rms value in the intermittent region of separation with control showed significant modifications based on each VG configuration suggesting the effectiveness of VG devices in controlling the amplitude of shock oscillations in such interactions.

Item Type: Article
Additional Information: Copyright for this article belongs to M/s. Multi-Science Publishing Co.,
Uncontrolled Keywords: Turbulent boundary layer;Freestream velocity;Pressure sensitive paint (PSP);Shock oscillations
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Aerodynamics
Depositing User: Ms. Alphones Mary
Date Deposited: 18 Mar 2014 09:46
Last Modified: 18 Mar 2014 09:46
URI: http://nal-ir.nal.res.in/id/eprint/11937

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