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A static compressible flow model of synthetic jet actuators

Published online by Cambridge University Press:  03 February 2016

H. Tang  and
S. Zhong
H. Tang
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, The University of Manchester, Manchester, UK
S. Zhong
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, The University of Manchester, Manchester, UK
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Abstract

In this paper, a simple static compressible flow model for circular synthetic jet actuators is described. It is used to undertake a systematic computational investigation of the effect of changing actuator geometrical and operating parameters on the magnitude of peak jet velocity at the orifice exit of an actuator whose diaphragm displacement and frequency are allowed to vary independently. It is found that, depending on the flow conditions inside the orifice duct, the actuator may operate in two distinct regimes, i.e. the Helmholtz resonance regime and the viscous flow regime. In the Helmholtz resonance regime, the resultant synthetic jet is generated by the mass physically displaced by the oscillating diaphragm coupled with the Helmholtz resonance in the actuator. In the viscous flow regime, the Helmholtz resonance is completely damped by viscous effect such that the jet is produced by the diaphragm oscillation alone. The relationship between actuator geometrical and operating parameters at the optimum condition which yields the maximum peak jet velocity at a given diaphragm displacement is also established for these two regimes. Finally, a preliminary procedure for designing synthetic jet actuators for flow separation control on an aircraft wing is proposed.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1121 , July 2007 , pp. 421 - 431
Copyright
Copyright © Royal Aeronautical Society 2007 

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