Hostname: page-component-78c5997874-v9fdk Total loading time: 0 Render date: 2024-11-05T04:03:24.070Z Has data issue: false hasContentIssue false
  • English
  • Français

Interaction of a Shock Wave with a Turbulent Boundary Layer Disturbed by Injection

Published online by Cambridge University Press:  07 June 2016

L.C. Squire  and
M.J. Smith
L.C. Squire
Affiliation:
Cambridge University Engineering Department
M.J. Smith
Affiliation:
Cambridge University Engineering Department
Get access

Summary:

An experimental investigation has been made to study the interaction between an incident oblique shock wave and a turbulent boundary layer on a solid surface downstream of a porous surface with air injection through the porous surface. The results are clearly of direct interest to the design of cooled turbine blades. However, the boundary-layer profiles in the absence of the shock are similar to those in a boundary layer subjected to an adverse pressure gradient so that the results at the interaction also give some indication of the effects of an isentropic compression upstream of a shock/boundary-layer interaction. The experiments show the surprising result that the shock strength to produce incipient Separation is virtually independent of the shape of the boundary-layer profile upstream of the interaction, although the scale of the interaction increases with increase in the injection rate.

Type
Research Article
Information
Aeronautical Quarterly , Volume 31 , Issue 2 , May 1980 , pp. 85 - 112
Copyright
Copyright © Royal Aeronautical Society. 1980

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 Marriott, P.G., Compressible turbulent boundary layers with discontinuous air transpiration, Aero. Res. Counc. R & M 3780, 1976 Google Scholar
2 Jeromin, L.O.F., An experimental investigation of compressible turbulent boundary layers with air injection. Aero. Res. Coun. R & M 3526, 1968 Google Scholar
3 Green, J.E., Reflection of an oblique shock wave by a turbulent boundary layer. J. Fluid Mech. 40, pp 81–96, 1970 Google Scholar
4 Smith, M.J., Interaction of a shock-wave with a boundary layer disturbed by injection. Ph.D. Dissertation, Cambridge University, 1977Google Scholar
5 Thomas, G.D., Compressible turbulent boundary layers with combined air injection and pressure gradient. Aero. Res. Coun. R & M 3779, 1976 Google Scholar
6 Peake, D.J., Brakmann, G. and Romeskie, J.M., Comparison between some high Reynolds number turbulent boundary layer experiments at Mach 4, and various recent calculation procedures. Paper 11 in AGARD Conference Proceedings 93, 1971 Google Scholar
7 Kuehn, D.M., Experimental investigation of the pressure rise required for incipient separation of turbulent boundary layers in two-dimensional supersonic flow. NASA Memo 1-21-59A, 1959 Google Scholar
8 Inger, G.R. and Zee, S., Transonic shockwave/turbulent-boundary-layer interaction with suction and blowing. J. of Aircraft, 15, pp 750–754, 1978 Google Scholar
9 Henderson, L.F., The reflexion of a shock wave at a rigid wall in the presence of a boundary layer. J. Fluid Meek., 30, pp 699–722, 1967 Google Scholar
10 Shapiro, A., The Dynamics and Thermodynamics of Compressible Flow. Vol. II. Ronald Press, 1954 Google Scholar