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The performance of round synthetic jets in quiescent flow

Published online by Cambridge University Press:  03 February 2016

M. Jabbal ,
J. Wu  and
S. Zhong
M. Jabbal
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, University of Manchester, Manchester, UK
J. Wu
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, University of Manchester, Manchester, UK
S. Zhong
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, University of Manchester, Manchester, UK
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Abstract

PIV measurements in the near-field region of a jet flow emanating from a round synthetic jet actuator into quiescent air were conducted over a range of operating conditions. The primary purpose of this work was to investigate the nature of synthetic jets at different operating conditions and to examine the jet flow parameters that dictate the behaviour of synthetic jet actuators. The effects of varying diaphragm displacement and oscillatory frequency for fixed actuator geometry were studied. It was observed that the characteristics of synthetic jets are largely determined by the Reynolds number and stroke length. An increase in the former is observed to increase the strength of consecutive vortex rings that compose a synthetic jet, whereas an increase in the latter results in an increase in relative vortex ring spacing and for further increases in stroke length, shedding of secondary vortices. Correlations were also made between the operating parameters and the performance parameters most effective for flow control and which therefore determine the impact of a synthetic jet on an external flow. Relations of time-averaged dimensionless mass flux, momentum flux and circulation with the jet flow conditions were established and found to widely support an analytical performance prediction model described in this paper. It is anticipated that the experimental data obtained in this study will also contribute towards providing a PIV database for macro-scale synthetic jet actuators.

Type
Research Article
Information
The Aeronautical Journal , Volume 110 , Issue 1108 , June 2006 , pp. 385 - 393
Copyright
Copyright © Royal Aeronautical Society 2006 

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