Hostname: page-component-78c5997874-mlc7c Total loading time: 0 Render date: 2024-11-03T05:43:00.234Z Has data issue: false hasContentIssue false
  • English
  • Français

Investigation of active control of swept shock wave/turbulent boundary-layer interactions – PSP results

Published online by Cambridge University Press:  03 February 2016

J. S. Couldrick ,
S. L. Gai ,
J. F. Milthorpe  and
K. Shankar
J. S. Couldrick
Affiliation:
School of Aerospace, Civil and Mechanical Engineering, University College, UNSW, Australian Defence Force Academy, Canberra, Australia
S. L. Gai
Affiliation:
School of Aerospace, Civil and Mechanical Engineering, University College, UNSW, Australian Defence Force Academy, Canberra, Australia
J. F. Milthorpe
Affiliation:
School of Aerospace, Civil and Mechanical Engineering, University College, UNSW, Australian Defence Force Academy, Canberra, Australia
K. Shankar
Affiliation:
School of Aerospace, Civil and Mechanical Engineering, University College, UNSW, Australian Defence Force Academy, Canberra, Australia
Get access Rights & Permissions [Opens in a new window]

Abstract

An investigation of active control of the swept shock wave/boundary-layer interaction using ‘smart’ flap actuators is presented. The actuators are manufactured by bonding piezoelectric material to an inert substrate to control the bLeed/suction rate through a plenum chamber. The cavity provides communication of signals across the shock, allowing rapid thickening of the boundary layer approaching the shock. This splits the shock foot into a series of weaker shocks forming a lambda structure, thus reducing wave drag. Active control allows optimisation of the unimorph deflection, hence rate of mass transfer.

In this paper, results of the interaction using pressure sensitive paint (PSP) are emphasised. It is shown that the use of PSP, in conjunction with discrete pressure data, enables the main features of the interaction to be observed when the actuators are subject to different deflections.

Type
Technical Note
Information
The Aeronautical Journal , Volume 108 , Issue 1087 , September 2004 , pp. 483 - 490
Copyright
Copyright © Royal Aeronautical Society 2004 

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. Alvi, A. and Settles, G.S. Physical model of the swept shock wave boundary-layer interaction flowfield, AIAA J, 1992, 30, (9), pp 2252–2258.Google Scholar
2. Green, J.E. Interactions between shock waves and turbulent boundary layers, Progress in Aerospace Science, (1969), 11, pp 253–340.Google Scholar
3. Koide, S., Saida, N. and Ogata, R. Correlation of separation angles induced by glancing iteractions, AIAA J, 1996, 34, (10 Technical Notes), pp 2198–2200.Google Scholar
4. Atkin, C.J., and Squire, L.C. A study of the interaction of a normal shock wave with a turbulent boundary layer at Mach numbers between 1·30 and 1·55, Eur J Mech, B/Fluids, 1992, 11, (1), pp 93–118.Google Scholar
5. Inger, G.R. Application of a shock-turbulent boundary layerinteraction theory in transonic flowfield analysis, 1981, AIAA Transonic Perspective Symposium, 18-20 February 1981, NASA/Ames Research Center, Moffett Field, California, USA.Google Scholar
6. Kubota, H. and Stollery, J.L. An experimental study of the interaction between a glancing shock wave and a turbulent boundary layer, J Fluid Mechanics, 1982, 116, pp 431–458.Google Scholar
7. Settles, G.S. and Dolling, D.S. Swept shock-wave/boundary layer interactions, Progress in Astronautics and Aeronautics, 1992, 141, (Seebass, A.R., Ed), pp 505–574.Google Scholar
8. Babinsky, H. Control of swept shock wave/turbulent boundary-layer interactions, 1999, ISSW22, July 18-23 1999, Imperial College, London.Google Scholar
9. Bahi, L., Ross, J.M. and Nagamatsu, H.T. Passive shock wave/boundary-layer control for transonic airfoil drag reduction, 1983, AIAA 21st Aerospace Sciences Meeting, January 1983, Reno, Nevada, USA.Google Scholar
10. Gibson, T.M., Babinsky, H. and Squire, L.C. Passive control of shock wave/boundary-layer interactions, Aeronaut J, 2000, 104, (1033), pp 129–140.Google Scholar
11. Nagamatsu, H.T., Ficarra, R.V. and Dyer, R. Supercritical airofoil drag reduction by passive shock wave/boundary-layer control in the Mach number range ·75 to ·90, 1985, AIAA 23rd Aerospace Sciences Meeting, January 1985, Reno, Nevada, USA.Google Scholar
12. Nagamatsu, H.T., Mitty, T.J. and Nyberg, G.A. Passive shock wave/boundary-layer control of a helicopter rotor airfoil in a contoured transonic wind tunnel, 1987, AIAA 25th Aerospace Sciences Meeting, January 1987, Reno, Nevada, USA.Google Scholar
13. Raghunathan, S. Effects of porosity strength on passive shockwave/boundary layer control, AIAA J, 1987, 25, (5), pp 757–758.Google Scholar
14. Raghunathan, S. Passive control of shock-boundary layer interaction, Progress in Aerospace Science, 1988, 25, pp 271–296.Google Scholar
15. Raghunathan, S., Gray, J.L. and Cooper, R.K. Effects of inclination of holes on passive shock wave boundary layer control, 1987, AIAA 25th Aerospace Sciences Meeting, January 1987, Reno, Nevada, USA.Google Scholar
16. Raghunathan, S. and Mabey, D.G. Passive shock-wave/boundary layer control on a wall-mounted model, AIAA J, 1987, 25, (2), pp 275–278.Google Scholar
17. Savu, G. and Trifu, O. Porous airfoils in transonic flow, AIAA J, 1984, 22, (7 Technical Notes), pp 989–991.Google Scholar
18. Couldrick, J.S., Gai, S., Milthorpe, J. and Shankar, K. Development of ‘smart’ flap actuators for swept shock wave boundary layer interaction control, 2001, Australian International Aerospace Conference, Canberra, Australia.Google Scholar
19. Couldrick, J.S., Gai, S., Milthorpe, J. and Shankar, K. Swept shock wave boundary layer interaction control with ‘smart’ flap actuators, 2002, 40th AIAA Aerospace Sciences Meeting and Exhibition, January 2002, Reno, Nevada, USA.Google Scholar
20. Couldrick, J.S., Gai, S., Milthorpe, J. and Shankar, K. Active control of swept shock wave/turbulent boundary layer interactions, Aeronaut J, 2004, 108, (1080), pp 93–101.Google Scholar
21. Couldrick, J.S., Gai, S.L., Milthorpe, J. and Shankar, K. Swept and normal shock wave/turbulent boundary layer interaction control with ‘smart’ flap actuators, 2003, CEAS Aerospace Aerodynamics Research Conference, 10-12 June 2003, RAeS, London, UK.Google Scholar
22. Couldrick, J.S., Shankar, K., Gai, S. and Milthorpe, J. Design optimisation of ‘smart’ flap actuators for swept shock wave boundary layer interaction control, 2002, 2nd Advances in Structural Engineering and Mechanics, 21-23 August 2002, Pusan, Korea.Google Scholar
23. Couldrick, J.S., Shankar, K., Gai, S. and Milthorpe, J. Design of ‘smart’ flap actuators for swept shock wave/turbulent boundary layer interaction control, Structural Engineering and Mechanics: An International Journal, 2003, 16, (5), pp 519–532.Google Scholar
24. Couldrick, J.S., Shankar, K., Gai, S. and Milthorpe, J. Structural design of ‘smart’ actuator flaps for control of shock wave boundary layer interactions, 2003, Advanced Technology in Experimental Mechanics, 10-12 September 2003, Nagoya, Japan.Google Scholar
25. Morris, M.J., Donovan, J.F., Kegelman, J.T., Schwab, S.D. and Levy, R.L. Aerodynamic applications of pressure sensitive paint, AIAA J, 1993, 31, (3), pp 419–425.Google Scholar
26. Klein, C. Application of pressure sensitive paint (PSP) for the determination of the instantaneous pressure field of models in a wind tunnel, Aerospace Science Technology, 2000, 4, pp 103–109.Google Scholar
27. Squire, L.C. Interaction of swept and unswept normal shock waves with boundary layers, AIAA J, 1996, 34, (10), pp 2099–2101.Google Scholar
28. Smith, A.N., Babinsky, H., Dhanaesekaran, P.C., Savill, A.M. and Dawes, W.N. Computational investigation of slot and groove controlled shock wave/boundary-layer interactions, 2003, AIAA Paper 03-0446, 41st AIAA Aerospace Sciences Meeting and Exhibition, 6-9 January 2003, Reno, Nevada, USA.Google Scholar
29. Smith, A.N., Babinsky, H., Fulker, J.L. and Ashill, P.R. Normal shock wave/turbulent boundary layer interactions in the presence of streamwise slots and gtrooves, Aeronaut J, 2002, 106, (1063), pp 493–500.Google Scholar