Hostname: page-component-7c8c6479df-r7xzm Total loading time: 0 Render date: 2024-03-29T22:56:31.464Z Has data issue: false hasContentIssue false

Cone cavity flow at M = 8·2 with injection of air and helium

Published online by Cambridge University Press:  04 July 2016

F. Bellone
Affiliation:
College of Aeronautics, Cranfield University, Bedford, UK
J. L. Stollery
Affiliation:
College of Aeronautics, Cranfield University, Bedford, UK

Abstract

An experimental investigation of cone cavity flow at M = 8·2 with injection of air and helium has been performed in the Cranfield University gun tunnel. The cone used had a 10° semi-angle and incorporated an annular cavity. The boundary layer ahead of the cavity was laminar. The study concentrated on the effects of increasing the mass injected into the cavity.

With no injection the external flow bridged the cavity. A shock wave and a pressure peak occurred at the rear face corner. By injecting gas, this pressure peak was decreased in intensity and a shock wave was formed at the front face corner. As the mass injected was increased, the shocks initially formed at the front and rear face corners were shifted upstream from their initial positions and boundary layer separation occurred ahead of the cavity. For the highest mass flow rate injected, the pressure peak at the rear face corner was very small. The cavity flow was never more than mildly unsteady.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society 1999 

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. Charwat, A.F. Roos, J.N. Dewey, F.C. and Hitz, J.A. An investigation of separated flows, part I: the pressure field, J Aero Sci, 1961, 28, (6).Google Scholar
2. Stallings, R.L. and Wilcox, F.J. Experimental cavity pressure distributions at supersonic speeds, NASA TP 2683, 1987.Google Scholar
3. Albacete, L.M. and Glowacki, W.J.S. Skin friction and heat transfer characteristics of the compressible laminar boundary layer with injection of a light, medium and heavy gas, NOL TR 66-215, March 1967.Google Scholar
4. Ginoux, J.J. and Thiry, F. Cone cavity flow at M = 5-3 with injection of light, medium and heavy gases, VKITN 35, Nov 1968.Google Scholar
5. Bellone, F. Cone Cavity Flow at M = 8·2 with Injection of Air and Helium, MSc Thesis, Cranfield University, College of Aeronautics, 1998.Google Scholar
6. Richards, B.E. Transitional and turbulent boundary layers on a cold flat plate in hypersonic flow, Aeronaut Q, 1967,18, (3).Google Scholar
7. AMES Research Staff Equations, tables and charts for compressible flow, NACA report 1135, 1953.Google Scholar
8. Batt, C.J. Investigation of Cavity Effects on an Axisymmetric Body in the Hypersonic Gun Tunnel, MSc Thesis, Cranfield University, College of Aeronautics, 1996.Google Scholar
9. Nicoll, K.M. Design Criteria and Experimental Techniques for a Study of a Hypersonic Cavity Flow with Mass Injection, Princeton University Report, Dept of Aeronautical Engineering, Dec 1964.Google Scholar
10. Powrie, H.E.G., Ball, G.J. and East, R.A. Comparison of the interaction of two and three dimensional transverse jets with a hypersonic stream, AGARD CP 534, 1993, pp 20.120.7.Google Scholar
11. Raush, J.R. and Roberts, B.B. Reaction control system aerodynamics interaction effects on Space Shuttle Orbiter, J Spacecraft, 1975, 12, pp 660666.Google Scholar