Hostname: page-component-586b7cd67f-t8hqh Total loading time: 0 Render date: 2024-11-23T21:53:34.246Z Has data issue: false hasContentIssue false
  • English
  • Français

Application of synthetic jet actuators for the modification of the characteristics of separated shear layers on slender wings

Published online by Cambridge University Press:  03 February 2016

M. Watson ,
A. J. Jaworski  and
N. J. Wood
M. Watson
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, The University of Manchester, Manchester, UK
A. J. Jaworski
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, The University of Manchester, Manchester, UK
N. J. Wood
Affiliation:
School of Mechanical, Aerospace and Civil Engineering, The University of Manchester, Manchester, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper presents an experimental investigation related to controlling the unsteady characteristics of the separated shear layers occurring over highly swept wings, and in particular focuses on application of synthetic jet actuators for modification of unsteady dynamic loading on the wing surface due to the phenomenon referred to as vortex breakdown (vortex burst).

In the post burst flow region the surface pressure measurements reveal the presence of certain characteristic spectral peaks that are thought to represent the presence of a spiralling filament of vorticity inside the expanded vortex that is known to be present in the burst flow over swept wings.

This paper details an investigation into how the use of an array of 18 discrete synthetic jet actuators, distributed along the leading edge of a delta wing with a 60° sweep angle, can be used to alter the spectral content of this unsteadiness and reduce the level of unsteady pressure found in the post-burst region toward the wing trailing edge by up to 40%.

Measurements of the surface pressure spectral distributions over the wing are presented together with PIV measurements of the vortex cross-section, conducted in the successive planes parallel to the wing trailing edge. Additional surface flow visualisation indicates that the effect of the actuators on the leading edge boundary layer is to induce local separation delays close to each actuator orifice, which introduce ‘ripples’ into the shear layer as it separates. The results obtained are used to formulate an interpretative hypothesis attempting to explain the mechanisms responsible for modification of the spectral content and the level of excitation measured on the wing surface.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1122 , August 2007 , pp. 519 - 529
Copyright
Copyright © Royal Aeronautical Society 2007 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Jaworski, A.J. A Study of Pressure Fluctuations caused by Vortex Breakdown, 1996, PhD thesis, Imperial College, London.Google Scholar
2. Lambourne, N.C. and Bryer, D.W. The bursting of leading edge vortices – some observations and discussion of the phenomenon, 1962, ARC R&M 3282, 22, (775).Google Scholar
3. Gad-El-Hak, M. and Blackwelder, R.F. Control of the discrete vortices from a delta wing, AIAA J, 1987, 25, (8), pp 1042–1049.Google Scholar
4. Mccormick, S. and Gursul, I. Effect of shear layer control on leading-edge vortices, J Aircr, 1996, 33, (6), pp 1087–1093.Google Scholar
5. Wood, N.J., Roberts, L. and Celik, Z. Control of asymmetric vortical flows over delta wings at high angles of attack, J Aircr, 1990, 27, (5), pp 429–435.Google Scholar
6. Guy, Y., Morrow, J.A. and Mclaughlin, T.E. Control of vortex breakdown on a delta wing by periodic blowing and suction, 1999, AIAA Paper 99-132.Google Scholar
7. Watson, M., Jaworski, A.J. and Wood, N.J. A study of synthetic jets from rectangular and dual-circular orifices, Aeronaut J, 2003, 107, (1073), pp 427–434.Google Scholar
8. Watson, M., Jaworski, A.J. and Wood, N.J. Contribution to the understanding of flow interactions between multiple synthetic jets, AIAA J, 2003, 41, (4), pp 747–749.Google Scholar
9. Amitay, M., Honohan, A., Trautman, M. and Glezer, A. Modification of the aerodynamic characteristics of bluff bodies using fluidic actuators, 1997, AIAA Paper 97-2004.Google Scholar
10. Smith, D.R., Amitay, M., Kibens, V., Parekh, D. and Glezer, A. Modification of lifting body aerodynamics using synthetic jet actuators, 1998, AIAA Paper 98-0209.Google Scholar
11. Watson, M., Jaworski, A.J. and Wood, N.J. The development of synthetic jets for enhanced control of separated flows, 2003, AIAA Paper 2003-3716.Google Scholar
12. Watson, M. The use of synthetic jet actuators for the enhanced control of Separated Flows, 2004, PhD thesis, The University of Manchester.Google Scholar
13. Woods, M.I. and Wood, N.J. Effect of sweep on buffet over novel wing planforms, J Aircr, 2000, 37, (5), pp 810–817.Google Scholar
14. Menke, M., Yang, H. and Gursul, I. Experiments in the unsteady nature of vortex breakdown over delta wings, Experiments in Fluids, 1999, 27, pp 262–272.Google Scholar
15. Sarpkaya, T. On stationary and travelling vortex breakdowns, J Fluid Mechanics, 1971, 45, pp 545–559.Google Scholar
16. Payne, F.M. The Structure of Leading Edge Vortex Flows including Vortex Breakdown, 1987, PhD thesis, University of Notre Dame.Google Scholar