Hostname: page-component-cd9895bd7-jkksz Total loading time: 0 Render date: 2024-12-28T06:43:11.087Z Has data issue: false hasContentIssue false
  • English
  • Français

The effect of the upstream boundary-layer state on the shock interaction at a compression corner

Published online by Cambridge University Press:  20 April 2006

Kiyotaka Hayakawa  and
L. C. Squire
Kiyotaka Hayakawa
Affiliation:
Cambridge University Engineering Department, Trumpington Street, Cambridge Present address: Gas Dynamics Laboratory, Princeton University, U.S.A.
L. C. Squire
Affiliation:
Cambridge University Engineering Department, Trumpington Street, Cambridge
Get access Rights & Permissions [Opens in a new window]

Abstract

In most experimental studies of the shock-wave/boundary-layer interaction at a compression corner the boundary layer upstream of the interaction has developed in zero-pressure-gradient conditions. However, in many practical situations the boundary layer upstream of the interaction is subject to adverse or favourable pressure gradients, and hence is in a non-equilibrium state. This paper presents the results of a series of experiments on the interaction at a compression corner where the boundary layer upstream of the corner is disturbed by air injected through a porous surface. The results are thus of direct interest to the design of transpiration-cooled aerodynamic surfaces. However, the boundary-layer profiles upstream of the interaction also have many similarities to those in an adverse pressure gradient, so that the results also give some indication of the effects of an isentropic compression upstream of the interaction. The results are used to discuss existing correlations for upstream influence and to study conditions for incipient separation. The experiments were made at Mach numbers of 1·8, 2·6, 2·7 and 2·9, with corner angles of 8°, 10°, 12°, 13° and 14°.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 122 , September 1982 , pp. 369 - 394
Copyright
© 1982 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

Appels, C. & Richards, B. E. 1975 Incipient separation of a compressible turbulent boundary layer. AGARD CP-168, Paper no. 21.
Bradshaw, P. & Unsworth, K. 1973 A note on Preston tube calibration in compressible flow. Imperial College, London, Rep. Aero. no. 73–07.
Chew, Y. T. & Squire, L. C. 1979 The boundary layer development downstream of a shock interaction at an expansion corner. Aero. Res. Counc. R. & M. no. 3839.
Chapman, D. R., Kuehn, D. M. & Larson, H. K. 1958 Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition. NACA Rep. no. 1356.Google Scholar
Van Driest, E. R. 1951 Turbulent boundary layer in compressible fluids. J. Aero. Sci. 18, 145.Google Scholar
Elfstrom, G. M. 1972 Turbulent hypersonic turbulent flow at a wedge compression corner. J. Fluid Mech. 53, 113.Google Scholar
Hopkins, E. J. 1972 Charts for predicting turbulent skin friction from the van Driest method (II). NACA TN D-6945.
Hunter, L. G. & Reekes, B. L. 1971 Results of a strong interaction, wakelike model of separated and reattaching turbulent flows. A.I.A.A. J. 9, 703.Google Scholar
Jeromin, L. O. F. 1966 An experimental investigation of compressible turbulent boundary layers with air injection. Aero. Res. Counc. R. & M. no. 3526.
Kessler, W. C., Reilly, J. F. & Mockapetris, L. J. 1970 Supersonic turbulent boundary layer interaction with an expansion ramp and a compression corner. McDonell-Douglas Rep. MDCE0264.Google Scholar
Kuehn, D. M. 1959 Experimental investigation of the pressure rise required for the incipient separation of turbulent boundary layers in two-dimensional supersonic flow. NACA Memo 1–21–59A (NACA/TIL/6209).
Law, C. H. 1974 Supersonic, turbulent boundary-layer separation. A.I.A.A. J. 12, 794.Google Scholar
Maltby, R. L. 1962 Flow visualization in wind tunnels using indicators. AGARDograph no. 70.
Popinski, Z. & Ehrlich, C. F. 1966 Development design method for predicting hypersonic aerodynamic control characteristics. U.S.A.F. Tech. Rep. AFFDL-TR-66–85, Wright Patterson A.F.B.Google Scholar
Roshko, A. & Thomke, G. J. 1969 Supersonic, turbulent boundary-layer interaction with a compression corner at very high Reynolds number. In Proc. Symp. on viscous Interaction Phenomena in Supersonic and Hypersonic Flow, Wright Patterson A.F.B., Ohio, p. 109. University of Dayton Press.
Roshko, A. & Thomke, G. J. 1976 Flare-induced interaction lengths in supersonic, turbulent boundary layers. A.I.A.A. J. 14, 873.Google Scholar
Rosen, R., Roshko, A. & Pavish, D. L. 1980 A two-layer calculation for the initial interaction region of an unseparated supersonic turbulent boundary layer with a ramp. A.I.A.A. Paper no. 80–0135.
Settles, G. S. & Bogdonoff, S. M. 1973 Separation of a supersonic turbulent boundary layer at moderate to high Reynolds numbers. A.I.A.A. Paper no. 73–666.
Settles, G. S., Bogdonoff, S. M. & Vas, I.E. 1976 Incipient separation of a supersonic turbulent boundary layer at high Reynolds numbers. A.I.A.A. J. 14, 50.Google Scholar
Smith, M. J., 1977 Interaction of a shock-wave with a boundary layer disturbed by injection. Ph.D. dissertation, Cambridge University.
Spaid, F. W. & Frishett, J. C. 1972 Incipient separation of a supersonic, turbulent boundary layer, including effects of heat transfer. A.I.A.A. J. 10, 915.Google Scholar
Spalding, D. B. & Chi, S. W. 1964 The drag of a compressible boundary layer on a smooth flat plate with and without heat transfer. J. Fluid Mech. 18, 117.Google Scholar
Squire, L. C. & Smith, M. J. 1980 Interaction of a shock wave with a boundary layer disturbed by injection. Aero. Q. 31, 85.Google Scholar
Winter, K. G. & Gaudet, L. 1970 Turbulent boundary-layer studies at high Reynolds numbers at Mach numbers between 02 and 28. Aero. Res. Counc. R. & M. no. 3712.