Hostname: page-component-745bb68f8f-d8cs5 Total loading time: 0 Render date: 2025-01-08T12:27:31.275Z Has data issue: false hasContentIssue false
  • English
  • Français

A supersonic turbulent boundary layer in an adverse pressure gradient

Published online by Cambridge University Press:  26 April 2006

Emerick M. Fernando  and
Alexander J. Smits
Emerick M. Fernando
Affiliation:
Department of Mechanical and Aerospace Engineering, Princeton University, Princeton, NJ 08544 USA
Alexander J. Smits
Affiliation:
Department of Mechanical and Aerospace Engineering, Princeton University, Princeton, NJ 08544 USA
Get access Rights & Permissions [Opens in a new window]

Abstract

This investigation describes the effects of an adverse pressure gradient on a flat plate supersonic turbulent boundary layer (Mf ≈ 2.9, βx ≈ 5.8, Reθ, ref ≈ 75600). Single normal hot wires and crossed wires were used to study the Reynolds stress behaviour, and the features of the large-scale structures in the boundary layer were investigated by measuring space–time correlations in the normal and spanwise directions. Both the mean flow and the turbulence were strongly affected by the pressure gradient. However, the turbulent stress ratios showed much less variation than the stresses, and the essential nature of the large-scale structures was unaffected by the pressure gradient. The wall pressure distribution in the current experiment was designed to match the pressure distribution on a previously studied curved-wall model where streamline curvature acted in combination with bulk compression. The addition of streamline curvature affects the turbulence strongly, although its influence on the mean velocity field is less pronounced and the modifications to the skin-friction distribution seem to follow the empirical correlations developed by Bradshaw (1974) reasonably well.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 211 , February 1990 , pp. 285 - 307
Copyright
© 1990 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

Alving, A. A. 1988 Boundary layer relaxation from curvature. Ph.D. thesis, Mechanical and Aerospace Engineering Department, Princeton University.
Ardonceau, P. L. 1984 The structure of turbulence in a supersonic shock wave/boundary layer interaction. AIAA J. 22, 1254–1262.Google Scholar
Bradshaw, P. 1967 Irrotational fluctuations near a turbulent boundary layer. J. Fluid Mech. 27, 209–230.Google Scholar
Bradshaw, P. 1973 The effect of streamline curvature on turbulent flow. AGAR Dograph 169. NATO.
Bradshaw, P. 1974 The effect of mean compression or dilatation on the turbulence structure of supersonic boundary layers. J. Fluid Mech. 63, 449–464.Google Scholar
Bradshaw, P. & Ferriss, D. H. 1971 Calculation of boundary-layer development using the turbulent energy equation: compressible flow on adiabatic walls. J. Fluid Mech. 46, 83–110.Google Scholar
Bradshaw, P. & Unsworth, K. 1974a An improved FORTRAN program for the Bradshaw-Ferriss-Atwell method of calculating turbulent shear layers. Aero Rep. 74–02. Imperial College, London.
Bradshaw, P. & Unsworth, K. 1974b Comment on ‘Evaluation of Preston tube calibration equations in supersonic flow’. AIAA J. 12, 1293–1295.Google Scholar
Carvin, C., Debieve, J. F. & Smits, A. J. 1988 The near wall temperature profile of turbulent boundary layers. AIAA Paper 88–0136.Google Scholar
Donovan, J. F. & Smits, A. J. 1987 A preliminary investigation of large-scale organized motions in a supersonic turbulent boundary layer on a curved surface. AIAA Paper 87–1285.Google Scholar
Dussauge, J.-P. & Quine, C. 1988 A second-order closure for supersonic turbulent flows. Application to the supersonic mixing. Symp. on The Physics of Compressible Turbulent Mixing, Princeton University, Princeton, N.J. Springer (to be published).
Favre, A. J. 1965 Review on space-time correlations in turbulent fluids. Trans. ASME E: J. Appl. Mech. 32, 261.Google Scholar
Fernando, E. M. 1988 Supersonic turbulent boundary layer in an adverse pressure gradient. Ph.D. thesis, Mechanical and Aerospace Engineering Department, Princeton University.
Fernando, E. M., Donovan, J. F. & Smits, A. J. 1987 The calibration and operation of a constant temperature cross-wire probe in supersonic flow. Symp. of Thermal Anemometry, Cincinnati, Ohio. ASME.
Fernholz, H. H., Smits, A. J., Dussauge, J. P. & Finley, P. J. 1988 A survey of measurements and measuring techniques in rapidly distorted compressible turbulent boundary layers. NATO Advisory Group for Aerospace Research and Development, AGARDograph 315.Google Scholar
Hayakawa, K., Smits, A. J. & Bogdonoff, S. M. 1984 Turbulence measurements in a compressible reattaching shear layer. AIAA J. 22, 889–895.Google Scholar
Hoffman, P. H., Muck, K. C. & Bradshaw, P. 1985 The effect of concave surface curvature on turbulent boundary layers. J. Fluid Mech. 161, 371–403.Google Scholar
Jayaram, M., Taylor, M. W. & Smits, A. J. 1987 The response of a compressible turbulent boundary layer to short regions of concave surface curvature. J. Fluid Mech. 175, 343–362.Google Scholar
Morkovin, M. V. 1961 Effects of compressibility on turbulent flows. In Mecanique de la Turbulence (ed. A. Favre). CNRS.
Muck, K. C., Hoffman, P. H. & Bradshaw, P. 1985 The effect of convex surface curvature on turbulent boundary layers. J. Fluid Mech. 161, 347–369.Google Scholar
Ramaprian, B. R. & Shivaprasad, B. G. 1978 The structure of turbulent boundary layers along mildly curved surfaces. J. Fluid Mech. 85, 273–303.Google Scholar
Settles, G. S. 1975 An experimental study of compressible turbulent boundary layer separation at high Reynolds numbers. Ph.D. thesis, Mechanical and Aerospace Engineering Department, Princeton University.
Smith, M. W. & Smits, A. J. 1988 A cinematic visualization of coherent density structures in a supersonic turbulent boundary layer. AIAA Paper 88–0500.Google Scholar
Smits, A. J., Hayakawa, K. & Muck, K. C. 1983 Constant temperature hot-wire practice in supersonic flows, Part I: The normal wire. Exp Fluids 1, 83–92.Google Scholar
Smits, A. J. & Dussauge, J. P. 1988 A survey of measurements and measurement techniques in rapidly distorted compressible turbulent boundary layers. AGARDograph 315, Chapter 5 (see Fernholz et al. 1988).
Smits, A. J., Alving, A. E., Smith, R. W., Spina, E. F., Fernando, E. M. & Donovan, J. F. 1988 A comparison of the turbulence structure of subsonic and supersonic boundary layers. Eleventh Symp. on Turbulence, University of Missouri-Rolla, October. (See also Phys. Fluids A 1, 1989. 1865–1875.)Google Scholar
Smits, A. J. & Joubert, P. N. 1982 Turbulent boundary layers on bodies of revolution. J. Ship Res. 26, 135–147.Google Scholar
Smits, A. J. & Muck, K. C. 1984 Constant temperature hot-wire anemometer practice in supersonic flows. Part II. The inclined wire. Exps Fluid 2, 33–41.Google Scholar
Smits, A. J. & Muck, K. C. 1987 Experimental study of three shock wave/turbulent boundary layer interactions. J. Fluid Mech. 182, 291–314.Google Scholar
Smits, A. J., Young, S. T. B. & Bradshaw, P. 1979 The effect of short regions of high surface curvature on turbulent boundary layers. J. Fluid Mech. 94, 209–242.Google Scholar
Spina, E. F. 1988 Organized structures in a supersonic turbulent boundary layer. Ph.D. thesis, Mechanical and Aerospace Engineering Department, Princeton University.
Spina, E. F. & Smits, A. J. 1987 Organized structures in a compressible turbulent boundary layer. J. Fluid Mech. 182, 85–109.Google Scholar
Taylor, M. W. 1984 A supersonic turbulent boundary layer on concavely curved surfaces. Princeton University Mechanical and Aerospace Engng Rep. 1684.Google Scholar
Van Driest, E. R. 1951 Turbulent boundary layer in compressible fluids. J. Aero. Sci. 18, 145–160 and 216.Google Scholar