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Passive control of shock wave–boundary-layer interactions

Published online by Cambridge University Press:  04 July 2016

T. M. Gibson ,
H. Babinsky  and
L. C. Squire
T. M. Gibson
Affiliation:
Aerodynamics Laboratory, Cambridge University Engineering Department, Cambridge, UK
H. Babinsky
Affiliation:
Aerodynamics Laboratory, Cambridge University Engineering Department, Cambridge, UK
L. C. Squire
Affiliation:
Aerodynamics Laboratory, Cambridge University Engineering Department, Cambridge, UK
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Abstract

The passive control of a shock wave-boundary-layer interaction involves placing a porous surface beneath the interaction, allowing high pressure air from the flow downstream of the shock wave to recirculate through a plenum chamber into the low pressure flow upstream of the wave.

The simple case of a normal shock wave at a Mach number of 1·4 interacting with the turbulent boundary layer on a flat wall is investigated both experimentally and numerically. The experimental investigation made use of holographic interferometry, while the computational section of the investigation made use of a Navier-Stokes code to derive pressure gradients, boundary-layer properties and total pressure losses in the interaction region. It is found that the structure of shock wave-boundary-layer interactions with passive control consists of a leading, oblique shock wave followed by a lambda foot. The oblique wave originates from the upstream end of the porous region, and its strength is determined by the magnitude of the local blowing velocities. The shape of the lambda foot depends on the position of the main shock relative to the control region, resembling an uncontrolled foot when the main shock wave is towards the downstream end of the porosity, but becoming increasingly large as the shock moves upstream and eventually merging with the leading, oblique shock to form a single, large, lambda structure.

Improved forms of passive control are suggested based on the findings of this investigation, including the use of passive control systems which incorporate streamwise variations in the level of porosity.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1033 , March 2000 , pp. 129 - 140
Copyright
Copyright © Royal Aeronautical Society 2000 

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References

1. 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, Euro J Mech B/Fluids, 1992, 11, (1), pp 93–118.Google Scholar
2. Délery, J. Shock wave-turbulent boundary layer interaction and its control, Progress in Aerospace Sciences, 1985, 22, pp 209–280.Google Scholar
3. Bahi, L., Ross, J.M. and Nagamatsu, H.T. Passive shock wave boundary layer control for transonic airfoil drag reduction, AIAA Paper 83-0137, 1983.Google Scholar
4. Nagamatsu, H.T., Ficarra, R.V. and Dyer, R. Supercritical Airfoil Drag Reduction by Passive Shock Wave-Boundary Layer Interaction Control in the Mach Number Range 0-75 to 0-90, AIAA Paper 85-0207, 1985.Google Scholar
5. Thiede, P. and Krogmann, P. Improvement of Transonic Airfoil Performance through Passive Shock-Boundary-Layer Interaction Control, IUTAM Symposium on Turbulent Shear-Layer-Shock wave Interactions, Palaiseau, France, 1985, pp 113–123.Google Scholar
6. Thiede, P. and Krogmann, P. Passive Control of Transonic Shock Boundary Layer Interaction, IUTAM Symposium Transsonicum III, Göttingen, 1988, pp 379–388.Google Scholar
7. Raghunathan, S. Pressure Fluctuation Measurements with Passive Shock/Boundary-Layer Control, AIAA J, 1987, 25, (4), pp 626–628.Google Scholar
8. Stanewsky, E., Délery, J., Fulker, J.L. and Geissler, W. (Eds) Euroshock — drag reduction by passive control, Notes on Numerical Fluid Mechanics, 1987, 56, Vieweg.Google Scholar
9. Raghunathan, S. Passive control of shock-boundary layer interaction, Progress in Aerospace Sciences, 1988, 25, pp 271–296.Google Scholar
10. Bur, R. Passive Control of a shock wave-turbulent boundary layer interaction in a transonic flow, La Recherche Aérospatiale, 1992-6, 11–30.Google Scholar
11. Raghunathan, S. and Mcilwain, S.T. Further investigations of transonic shock wave-boundary-layer interaction with passive control, J Aircr, 1990, 27, (1), pp 60–65.Google Scholar
12. Chokani, N. and Squire, L.C. Passive control of shock-boundary layer interactions: numerical and experimental studies, IUTAM Symposium Transsonicum III, Göttingen, 1988, pp 399–406.Google Scholar
13. Bur, R. and Délery, J. Study of passive control applied to a transonic shock wave-boundary layer interaction, ONERA Report RT107/7078 AY, Euroshock Report TR AER 2-92-49/1.4, 1996.Google Scholar
14. Chokani, N. and Squire, L.C. Transonic shockwave-turbulent boundary layer interactions on a porous surface, Aeronaut J, May 1993, 97, (965), pp 163–170.Google Scholar
15. Gibson, T.M. The Passive Control of Shock Wave-Boundary-Layer Interactions, PhD Thesis, University of Cambridge, 1997.Google Scholar
16. Yeung, A.F.K. The Passive Control of Swept-Shock-Boundary-Layer Interactions, PhD Thesis, University of Cambridge, 1994.Google Scholar
17. Baldwin, B. and Lomax, H. Thin layer approximation and algebraic model for separated turbulent flows, AIAA Paper 78-257, 1978.Google Scholar
18. Jameson, A. and Baker, T.J. Multigrid Solution of the Euler Equations for Aircraft Configurations, AIAA Paper 84-0093, 1984.Google Scholar
19. Dawes, W.N. A numerical analysis of the three-dimensional viscous flow in a transonic compressor rotor and comparison with experiment, J Turbomachinery, 1987, 109, pp 83–90.Google Scholar
20. Babinsky, H., Meguro, T., Jiang, Z. and Takayama, K. Numerical Visualisation of Shock Wave Flow in an Expanding Tube and Comparison with Experiment, ASME FED Vol 28, Experimental and Numerical Flow Visualisation, 1995, pp 89–94.Google Scholar
21. Green, J.E. Interactions between shock waves and turbulent boundary layers, RAE TR 69098, 1969.Google Scholar
22. Bur, R. Etude fondamentale sur le controle passif de l'interaction onde de choc/couche limite turbulente en ecoulement transsonique, PhD Thesis, University of Paris 6, 1991.Google Scholar