Hostname: page-component-78c5997874-fbnjt Total loading time: 0 Render date: 2024-11-03T05:31:42.798Z Has data issue: false hasContentIssue false
  • English
  • Français

Experiments on the hypersonic turbulent shock-wave/boundary-layer interaction and the effects of surface roughness

Published online by Cambridge University Press:  03 February 2016

S. A. Prince ,
M. Vannahme  and
J. L. Stollery
S. A. Prince
Affiliation:
Centre for Aeronautics, City University, London
M. Vannahme
Affiliation:
College of Aeronautics, Cranfield University, Cranfield, UK
J. L. Stollery
Affiliation:
College of Aeronautics, Cranfield University, Cranfield, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

An experimental investigation was performed to study the effects of surface roughness on the Mach 8·2 hypersonic turbulent shockwave–boundary-layer interaction characteristics of a deflected control flap configuration. In particular, the surface pressure and heat transfer distribution along a quasi-2D ramp compression corner model was measured for flap angles between 0° and 38°, along with a Schlieren flow visualisation study. It was found that surface roughness, of scale 10% of the hinge-line boundary layer thickness, significantly increased the extent of the interaction, while increasing the magnitude of the peak pressure and heat flux just aft of reattachment. The incipient separation angle for a fully turbulent, Mach 8·2 boundary layer with a hinge line Reynolds number of 1·44 × 106, was estimated at 28-29°, reducing to between 19-22° with the introduction of laminar sub-layer scale surface roughness.

Type
Research Article
Information
The Aeronautical Journal , Volume 109 , Issue 1094 , April 2005 , pp. 177 - 184
Copyright
Copyright © Royal Aeronautical Society 2005 

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. Prince, S.A., Vannahme, M. and Stollery, J.L.. Experiments on the hypersonic turbulent shock-wave/boundary layer interaction and the effects of surface roughness, January 1999, AIAA Paper 99-0147.Google Scholar
2. Prince, S.A.. Hypersonic Turbulent Interaction Phenomena and Control Flap Effectiveness, 1995, MSc thesis, Cranfield College of Aeronautics.Google Scholar
3. Elfstrom, G.M.. Turbulent separation in hypersonic flow, 1971, I.C. Aero Report 71-16, Dept of Aeronautics, Imperial College of Science & Technology.Google Scholar
4. Elfstrom, G.M.. Turbulent hypersonic flow at a wedge-compression corner, J Fluid Mech, 1972, 53, pp 113–127.Google Scholar
5. Coleman, G.T.. Hypersonic Turbulent Boundary Layer Studies, March 1973, PhD Thesis, Department of Aeronautics, Imperial College of Science & Technology.Google Scholar
6. Stollery, J.L. and Coleman, G.T.. A correlation between pressure and heat transfer distributions at supersonic and hypersonic speeds, Aero Q, November 1975, pp 304–312.Google Scholar
7. Coleman, G.T. and Stollery, J.L.. Heat transfer from hypersonic shock wave/turbulent boundary layer interactions, J Fluid Mech, 1972, 56, pp 741–752.Google Scholar
8. Bogdonoff, S.M. and Kepler, C.E.. Separation of a supersonic turbulent boundary layer, J Aero Sciences, June 1955, pp 414–424.Google Scholar
9. Holden, M.S.. Shock-wave/turbulent boundary layer interaction in hypersonic flow, January 1977, AIAA Paper 77-45.Google Scholar
10. Spaid, F.W. and Frishnett, J.C.. Incipient separation of a supersonic turbulent boundary layer including effects of heat transfer, AIAA J, July 1972, 10, (7), pp 915–922.Google Scholar
11. Batham, J.P.. An experimental study of turbulent separating & reattaching flows at a high Mach number, J Fluid Mech, 1972, 52, Part 3, pp 425–435.Google Scholar
12. Miller, D.S., Hijman, R. and Childs, M.E.. Mach 8 to 22 studies of flow separation due to deflected control surfaces, AIAA J, February 1964, 2, (2).Google Scholar
13. Knight, D., Yan, H., Panaras, A. and Zheltovodov, A.. Advances in CFD prediction of shock wave turbulent boundary layer interactions, Prog in Aerospace Sci, February/April 2003, 39, (2-3), pp 121–184.Google Scholar
14. Schlichting, H., Boundary Layer Theory, Chapter XI, 1956, McGraw-Hill.Google Scholar
15. Bertin, J.J., Hayden, T.E. and Goodrich, W.D.. Shuttle boundary layer transition due to distributed roughness and surface cooling, J Spacecraft & Rockets, September-October 1982, 19, (5), pp 389–396.Google Scholar
16. Disimile, P.J. and Scaggs, N.E.. An investigation into wedge induced turbulent boundary layer separation on a uniformly roughened surface at Mach 6, 1989, AIAA 89-2163-CP, pp 32-41, Proceedings of the Seventh AIAA Applied Aerodynamics Conference, 31 July-2 August, 1989, Seattle, Washington.Google Scholar
17. Christoph, G.H. and Fiore, A.W.. Numerical simulation of flow over rough surfaces including effects of shock waves, February 1975, ARL Tech Report 75-0028.Google Scholar
18. Babinsky, H.. A Study of Roughness in Turbulent Hypersonic Boundary Layers, 1993, PhD thesis, Cranfield University.Google Scholar
19. McConnell, A.D.. Roughness effects on impinging shock wave/turbulent boundary layer interactions, August 1999, MPhil thesis, Cambridge University.Google Scholar
20. Babinsky, H., Inger, G.R. and McConnell, A.D.. A basic experimental/theoretical study of rough wall turbulent shock/boundary layer interaction, 1999, Paper 0050, Proceedings of the 22nd International Symposium on Shock Waves, Imperial College, London, 18-23 July, 1999.Google Scholar