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The behaviour of circular synthetic jets in a laminar boundary layer

Published online by Cambridge University Press:  03 February 2016

S. Zhong ,
F. Millet  and
N. J. Wood
S. Zhong
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, Manchester University, UK
F. Millet
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, Manchester University, UK
N. J. Wood
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, Manchester University, UK
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Abstract

Dye flow visualisation of circular synthetic jets was carried out in laminar boundary layers developing over a flat plate at a range of actuator operating conditions and freestream velocities of 0·05 and 0·1ms–1. The purpose of this work was to study the interaction of synthetic jets with the boundary layer and the nature of vortical structures produced as a result of this interaction. The effects of Reynolds number (Re), velocity ratio (VR) and Strouhal number (St) on the behaviour of synthetic jets were studied. At low Re and VR, the vortical structures produced by synthetic jets appear as highly stretched hairpin vortices attached to the wall. At intermediate Re and VR, these structures roll up into vortex rings which experience a considerable amount of tilting and stretching as they enter the boundary layer. These vortex rings will eventually propagate outside the boundary layer hence the influence of the synthetic jets on the near wall flow will be confined in the near field of the jet exit. At high Re and VR, the vortex rings appear to experience a certain amount of tilting but no obvious stretching. They penetrate the edge of the boundary layer quickly, producing very limited impact on the near wall flow. Hence it is believed that the hairpin vortices produced at low Re and VR are likely to be the desirable structures for effective flow separation control. In this paper, a vortex model was also described to explain the mechanism of vortex tilting.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 109 , Issue 1100 , October 2005 , pp. 461 - 470
Copyright
Copyright © Royal Aeronautical Society 2005 

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