Hostname: page-component-7b7567c8c-7pwfn Total loading time: 0 Render date: 2026-11-15T18:25:54.496Z Has data issue: false hasContentIssue false
  • English
  • Français

Supersonic cooling by shock–vortex interaction

Published online by Cambridge University Press:  26 April 2006

M. D. Fox and
M. Kurosaka
M. D. Fox
Affiliation:
Department of Aeronautics and Astronautics, University of Washington, Seattle, WA 98195-2400, USAPresent address: Solar Turbines Inc., San Diego, CA 92186-5376, USA.
M. Kurosaka
Affiliation:
Department of Aeronautics and Astronautics, University of Washington, Seattle, WA 98195-2400, USA
Get accessRights & Permissions [Opens in a new window]

Abstract

The subject of total temperature separation in jets was treated in Fox et al. (1993) for subsonic jets. When we extended this study to the case of supersonic jets, we found the presence of a different mechanism of cooling, an effect which does not appear to have been known in the past. Named the ‘shock-induced total temperature separation’, this cooling can be of much greater magnitude than the subsonic cooling treated previously; it is caused by the interaction of convected vortical structures near the jet exhaust with the shock structure of the supersonic jet.

In studying this phenomenon, we focus our attention on overexpanded jets exiting a convergent-divergent nozzle. The theoretical results for the shock-induced cooling which are based on a linearized, unsteady supersonic analysis are shown to agree favourably with experiments.

When an impingement plate is inserted, the shock-induced cooling would manifest itself as wall cooling, whose magnitude is significantly larger than the subsonic counterpart. This has implications for heat transfer not only in jets, but wherever vortical structures may interact with shock waves.

Information

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 308 , 10 February 1996, pp. 363 - 379
Copyright
© 1996 Cambridge University Press

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

Ahuja, K. K., Massey, K. C., Fleming, A. J., Tam, C. K. W. & Jones, R. R. 1992 AEDEC-TR-91-20, AD-A245 463, Arnold Engineering Development Center, Arnold Air Force Base, Tennessee, Air Force Systems Command, US Air Force.
Carrier, G. F. 1949 J. Aero. Sci. 16, 150–152.
Érdelyi, A. (Ed.) 1954 Tables of Integral Transforms, vol. 1, p. 250. McGraw-Hill.
Fox, M. D. 1994 The effect of large-scale vortical structures on the heat transfer from a surface. PhD dissertation, Department of Aeronautics and Astronautics, University of Washington, Seattle, Washington, USA.
Fox, M. D., Kurosaka, M., Hedges, L. & Hirano, K. 1993 J. Fluid Mech. 255, 447–472 (and corrigendum, 261, 1944, 376).
Kurosaka, M. 1974 J. Fluid Mech. 62, 811–827.
Kurosaka, M. 1977 J. Fluid Mech. 83, 751–773.
Kurosaka, M., Gertz, J. B., Graham, J. E., Goodman, J. R., Sundaram, P., Riner, W. C., Kuroda, H. & Hankey, W. L. 1987 J. Fluid Mech. 178, 1–29.
Lepicovsky, J., Ahuja, K. K., Brown, W. H. & Burrin, R. H. 1986 AIAA Paper 86-1941.
Ng, W. F., Chakroun, W. M. & Kurosaka, M. 1990 Phys. Fluids A 2, 971–978.
O'Callaghan, J. J. & Kurosaka, M. 1993 AIAA J. 31, 1157–1159.
Seiner, J. M., Manning, J. C. & Ponton, M. K. 1986 AIAA Paper 86-1942.
Suda, H., Manning, T. A. & Kaji, S. 1993 AIAA Paper 93-4323.
Summerfield, M., Foster, C. R. & Swan, W. C. 1954 Jet Propulsion 24, 319–321.
Tam, C. K. W. 1991 In Aeroacoustics of Flight Vehicles: Theory and Practice. Vol. 1: Noise Sources (ed. H. H. Hubbard), chap. 6. NASA Reference Publication 1258, Vol. 1: WRDC Technical Report 90–3052.
Tam, C. K. W. & Burton, D. E. 1984 J. Fluid Mech. 138, 273–295.
Troutt, T. R. & McLaughlin, D. K. 1982 J. Fluid Mech. 116, 123–156.