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Computational investigation of cavity flow control using a passive device

Published online by Cambridge University Press:  27 January 2016

B. Khanal ,
K. Knowles  and
A. J. Saddington
B. Khanal*
Affiliation:
Department of Engineering Science, University of Oxford, Oxford, UK
K. Knowles*
Affiliation:
Aeromechanical Systems Group, Cranfield University, Shrivenham, UK
A. J. Saddington*
Affiliation:
Aeromechanical Systems Group, Cranfield University, Shrivenham, UK
*
[email protected]
[email protected]
[email protected]
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Abstract

In this paper, flow control effectiveness of a passive device in relation to open cavity flowfield is investigated computationally and compared with experimental work. Specifically the modification in the cavity flowfield due to the presence of a spoiler is studied in details to explain the physics behind the flow control effects. A combination of 2D and 3D flow visualisation tools are used to understand the flow behaviour inside the cavity and the quantitative analysis of the unsteady pressure fluctuations is also performed to assess the unsteady effects. Flow simulations with a turbulence model based on a hybrid RANS/LES (commonly known as Detached-Eddy Simulation (DES)) are used in this study. The time-mean flow visualisation clearly showed the presence of three dimensional effects inside the empty cavity whereas the 3D effects were found to diminish in the presence of a spoiler. In the unsteady flow analysis, near-field acoustic spectra were computed for empty cavity as well as cavity-with-spoiler cases. Study of unsteady pressure spectra for the cavity-with-spoiler case was found to record the complete suppression of the dominant tones in the presence of the spoiler. The analysis has indicated that the main reason behind this suppression is due to the inability of faintly energised vortical structures (faintly energised as a result of the extraction of turbulent kinetic energy by the spoiler) to maintain the unsteady flapping of the separated shear layer.

Type
Research Article
Information
The Aeronautical Journal , Volume 116 , Issue 1176 , February 2012 , pp. 153 - 174
Copyright
Copyright © Royal Aeronautical Society 2012 

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