Hostname: page-component-cd9895bd7-mkpzs Total loading time: 0 Render date: 2024-12-19T07:04:02.718Z Has data issue: false hasContentIssue false
  • English
  • Français

Turbulent shear layer reattachment downstream of a backward-facing step in confined supersonic axisymmetric flow

Published online by Cambridge University Press:  29 March 2006

T. Mukerjee  and
B. W. Martin
T. Mukerjee
Affiliation:
Mechanical Engineering Department, Imperial College, London
B. W. Martin
Affiliation:
Mechanical and Production Engineering Department University of Wales Institute of Science and Technology, Cardiff
Get access Rights & Permissions [Opens in a new window]

Abstract

The reattachment of a supersonic jet with a turbulent boundary layer abruptly expanding into an axisymmetric parallel diffuser has been experimentally investigated using a surface-flow technique. Measurements were made in the started condition, where the blowing pressure is sufficiently high to establish an oblique shock system in the diffuser. The proposed reattachment criterion correlates present measurements in terms of the diffuser area ratio, and also those of other workers for unconfined flow in terms of the free stream Mach number after separation. As already reported for unconfined flow, it is found that disturbances downstream of reattachment do not affect the upstream region.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 39 , Issue 2 , 10 November 1969 , pp. 307 - 319
Copyright
© 1969 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.)

References

Anderson, J. S. & Williams, T. J. 1968 J. Mech. Engng Sci. 10, 262.
Baker, P. J. & Martin, B. W. 1965 J. Mech. Engng Sci, 7, 15.
Bauer, R. C. 1964 AEDC-TDR-64-3.
Bogdonoff, S. M., Kepler, C. E. & Sanlorenze, E. 1953 Princeton University Aero. Rep. no. 222.
Carriere, P. & Sirieix, M. 1964 ONERA, Tiré a, Part 165.
Delery, J. 1965 La Recherche Aerospatiale no. 104, 15.
Hastings, R. C. 1963 R.A.E. T.N.Aero. no. 2931.
Korst, H. H. 1956 J. Appl. Math. 23, 593.
Korst, H. H., Chow, W. L. & Zumwalt, G. W. 1959 University of Illinois ME-TN-392-5.
Martin, B. W. & Baker, P. J. 1963 J. Mech. Engng Sci. 5, 98.
Martin, B. W. & Mukerjee, T. 1968 Proc. I. Mech. E. 182, 3H, 209.
Mcdonald, H. 1964 Aero. Quart. 15, 247.
Mukerjee, T. 1968 Ph.D. Thesis, University of London.
Nash, J. F. 1962 A.R.C. R. & M. no. 3344.
Page, R. H., Kessler, T. J. & Hill, W. G. 1967 ASME Paper no. 67-FE-20.
Przirembel, C. E. G. & Page, R. H. 1968 Proc. Heat. Transfer and Fluid Mechanics Institute, 258.
Roberts, J. B. 1964 N.G.T.E. Rep. no. R. 265.
Roshko, A. & Thomke, G. J. 1966 AIAA J. 4, 975.
Sirieix, M., Mirande, J. & Delery, J. 1966 AGARD CP no. 4, 353.
Tucker, M. 1951 NACA TN no. 2337.