Hostname: page-component-6bb9c88b65-6vlrh Total loading time: 0 Render date: 2025-07-28T00:36:30.273Z Has data issue: false hasContentIssue false
  • English
  • Français

Alleviation of shock oscillations in transonic flow by passive controls

Published online by Cambridge University Press:  04 July 2016

S. Raghunathan ,
D. E. Hall  and
D. G. Mabey
S. Raghunathan
Affiliation:
Queen's University of Belfast
D. E. Hall
Affiliation:
Queen's University of Belfast
D. G. Mabey
Affiliation:
Royal Aerospace Establishment, Bedford
Get access Rights & Permissions [Opens in a new window]

Abstract

Passive control experiments were made on an 18% thick biconvex aerofoil model in Mach number range giving shock oscillations and at a Reynolds number of 0.7 x 106 with fixed boundary layer transition. The control methods studied included a passive control of shock wave boundary layer interaction by a porous surface and a cavity, and a buffet breather made of holes connecting upper and lower surfaces of the aerofoil. The experiments show that the shock oscillations can be virtually eliminated by these methods. A physical explanation is given for the success of these passive controls.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 94 , Issue 937 , September 1990 , pp. 245 - 250
Copyright
Copyright © Royal Aeronautical Society 1990 

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.)

Article purchase

Temporarily unavailable

References

1. Mabey, D. G. Prediction of the Severity of Buffeting, Paper 7. AGARD LS 94, 1978.Google Scholar
2. Tijdeman, H. Investigation of the Transonic Flow Around Oscillating Aerofoils, NLR-77-090U, 1977.Google Scholar
3. Finke, K. Shock Oscillations in Transonic Flow, VDI Fors-chungsheft 580, 1977.Google Scholar
4. McDevitt, J. B., Levy, L. L. and Deiwart, G. S. Transonic flow about a thick circular aerofoil, AIAA J. 1976, 14, (5), pp 606–613.Google Scholar
5. Seegmiller, H. L., Marvin, J. G. and Levy, L. L. Steady and unsteady transonic flow, AIAA J, 1978, 16, (12), pp 1262–1270.Google Scholar
6. Mabey, D. G. Oscillatory flow from shock induced separation of biconvex aerofoils of varying techniques in ventilated wind tunnels. Proceedings of AGARD Conference on Boundary Layer Effects on Unsteady Air Loads, Aix-en-Provence, Sept 1980.Google Scholar
7. Mabey, D. G., Welsh, B. L. and Cripps, B. E. Periodic Flows on a Rigid 14% Thick Biconvex Wing at Transonic Speeds, RAE TN 81059, 1981.Google Scholar
8. Mabey, D. G. and Lee, P. Reduction of Low Frequency buffet from a Bluff Body at Transonic Speeds, RAE TM 2030, 1985.Google Scholar
9. Gibb, J. The Cause and Cure of Periodic Flows at Transonic Speeds, ICAS, 1988. Paper 3.10.1.Google Scholar
10. Mabey, D. G. and Raghunathan, S. Buffet Breathers for Aerofoils, UK Patent Application No. 8600175, 1986.Google Scholar
11. Bahi, L., Ross, J. M. and Nagamatsu, H. T. Passive Shock Wave/Boundary Layer Control for Transonic Aerofoil Drag Reduction, AIAA Paper 83 - 0137, 1983.Google Scholar
12. Krogman, P., Stanewsky, E. and Theide, P. Effect of suction on shock/boundary layer interaction and shock induced separation, J Aircraft, 1985, 22, pp.37–42.Google Scholar
13. Raghunathan, S. and Mabey, D. G. Passive Shock Wave/Boundary Layer Control on a Circular Arc Model. AIAA 86 - 0285.Google Scholar
14. Chen, C. L., Chow, Y. C., van dalsem, W. R. and Holst, T. L. Computation of Viscous Transonic Flow Over Porous Aerofoils, AIAA 87 - 0359, 1987.Google Scholar
15. Raghunathan, S. Passive control of shock/boundary layer interaction, Prog Aerosp Sci, 1988, 25, pp 271–296.Google Scholar
16. Mabey, D. G. Resonance Frequencies of Ventilated Wind Tunnels, R&M 3841, 1978.Google Scholar
17. Theide, P., Krogmann, P. and Stanewsky, E. Active and Passive Shock Boundary/Layer Interaction on Supercritical Aerofoil. AGARD-CP-365, Paper 23, 1984.Google Scholar
18. Mabey, D. G. Some aspects of aircraft dynamic loads due to flow separation. Prog Aerosp Sci, 1989, 26, pp 115–151.Google Scholar