Hostname: page-component-848d4c4894-hfldf Total loading time: 0 Render date: 2024-06-01T21:54:06.363Z Has data issue: false hasContentIssue false
  • English
  • Français

The structure of a supersonic turbulent boundary layer subjected to concave surface curvature

Published online by Cambridge University Press:  26 April 2006

John F. Donovan ,
Eric F. Spina  and
Alexander J. Smits
John F. Donovan
Affiliation:
McDonnell Douglas Aerospace, St Louis, MO 63166, USA
Eric F. Spina
Affiliation:
Syracuse University, Mechanical and Aerospace Engineering Department, Syracuse, NY, USA
Alexander J. Smits
Affiliation:
Princeton University Gas Dynamics Laboratory Princeton, NJ 08544, USA
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper reports an experimental investigation of the instantaneous structure of a supersonic turbulent boundary layer (M = 2.86, Reθ = 82000) over a short region of longitudinal concave surface curvature. The radius of curvature was 12 initial boundary-layer thicknesses and the turning angle was 16°. Severe distortion of the boundary layer occurred, as evidenced by an alteration of the mean velocity profiles and an increase in wall shear stress of 125%. The large-scale organized motions in the boundary layer were significantly altered as illustrated by changes in the character of the mass flux ‘fronts’ (large gradients in the fluctuating streamwise mass flux).

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 259 , 25 January 1994 , pp. 1 - 24
Copyright
© 1994 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. E. 1988 Boundary layer relaxation from convex curvature. PhD thesis, Princeton University.
Blackwelder, R. & Kaplan, R. E. 1976 On the wall structure of the turbulent boundary layer. J. Fluid Mech. 76, 89–112.Google Scholar
Bradshaw, P. 1973 The effect of streamline curvature on turbulent flow. NATO Advisory Group for Aerospace Research and Development, AGARD ograph 169.
Bradshaw, P. & Unsworth, K. 1974a Comment on evaluation of Preston tube calibration equations in supersonic flow. AIAA J. 12, 1293–1295.Google Scholar
Bradshaw, P. & Unsworth, K. 1974b An improved Fortran program for the Bradshaw–Ferris-Atwell method of calculating turbulent shear layers. Imperial College Aero Rep. 74-02.
Chou, J. H. & Childs, M. E. 1983 An experimental study of surface curvature effects on a supersonic turbulent boundary layer. AIAA Paper 83-1672.
Clauser, F. H. 1954 Turbulent boundary layers in adverse pressure gradients. J. Aeronaut. Sci. 21, 91–108.Google Scholar
Donovan, J. F. & Spina, E. F. 1992 An improved analysis method for crossed-wire signals obtained in supersonic flow. Exps Fluids 12, 359–368.Google Scholar
Donovan, J. F. 1989 The structure of supersonic turbulent boundary layers subjected to concave surface curvature. PhD thesis, Princeton University, Princeton, NJ.
Fernando, E. M. 1988 The effects of an adverse pressure gradient on a flat plate supersonic, turbulent boundary layer. PhD thesis, Princeton University, Princeton, NJ.
Fernando, E. M. & Smits, A. J. 1990 A supersonic turbulent boundary layer in an adverse pressure gradient. J. Fluid Mech. 211, 343–362.Google Scholar
Fernholz, H. H. & Finley, P. J. 1980 A critical commentary on mean flow data for two-dimensional compressible turbulent boundary layers. NATO Advisory Group for Aerospace Research and Development, AGARDograph 253.
Fernholz, H. H., Finley, P. J., Dussauge, J. P. & Smits, A. J. 1989 A survey of measurements and measuring techniques in rapidly distorted compressible turbulent boundary layers. NATO Advisory Group for Aerospace Research and Development, AGARDograph 315.
Gaviglio, J. 1987 Reynolds analogies and experimental study of heat transfer in the supersonic boundary layer. Intl J. Heat Mass Transfer 30, 911–926.Google Scholar
Hayakawa, K., Smits, A. J. & Bogdonoff, S. M. 1984 Hot-wire investigation of an unseparated shock-wave/turbulent boundary layer interaction. AIAA J. 22, 579–585.Google Scholar
Head, M. R. & Bandyopadhyay, P. 1981 New aspects of turbulent boundary layer structure. J. Fluid Mech. 107, 297–338.Google Scholar
Hoydysh, W. G. & Zakkay, V. 1969 An experimental investigation of hypersonic turbulent boundary layers in adverse pressure gradient. AIAA J. 7, 105–116.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
Laderman, A. J. 1980 Adverse pressure gradient effects on supersonic boundary layer turbulence. AIAA J. 18, 1186–95.Google Scholar
McLafferty, G. H. & Barber, R. E. 1962 The effect of adverse pressure gradient on the characteristics of turbulent boundary layers in supersonic streams. J. Aero. Sci. 29, 1–10.Google Scholar
Morkovin, M. V. 1962 Effects of compressibility on turbulent flows. Intl Symp. on the Mechanics of Turbulence, CNRS, Paris.Google Scholar
Morkovin, M. V. 1992 Mach number effects on free and wall turbulent structures in light of instability flow interactions. In Studies in Turbulence (ed. T. B. Gatski, S. Sarkar & C. J. Speziale). Springer.
Owen, F. K. & Hortsman, C. C. 1972 On the structure of hypersonic turbulent boundary layers. J. Fluid Mech. 53, 611.Google Scholar
Settles, G. S. & Teng, H. Y. 1982 Flow visualization of separated three-dimensional shock wave/turbulent boundary layer interactions. AIAA Paper 82-0029.
Smith, D. R. 1993 The response of a turbulent boundary layer in supersonic flow to successive distortions. PhD thesis, Princeton University.
Smith, D. R., Fernando, E. M., Donovan, J. F. & Smits, A. J. 1992 Conventional skin friction measurement techniques for strongly perturbed supersonic turbulent boundary layers. Eur. J. Mech B 11, 719–740.Google Scholar
Smith, D. R. & Smits, A. J. 1993 Direct measurements of the velocity and temperature field in turbulent boundary layers at Mach 3. Expl Thermal Fluid Sci. (to appear).Google Scholar
Smith, M. W. & Smits, A. J. 1988 Cinematic visualization of coherent density structures in a supersonic turbulent boundary layer. AIAA Paper 88-0500.
Smits, A. J., Eaton, J. A. & Bradshaw, P. 1979a The response of a turbulent boundary layer to lateral divergence. J. Fluid Mech. 94, 243–268.Google Scholar
Smits, A. J., Hayakawa, K. & Muck, K. C. 1983 Constant temperature hot-wire anemometry practice in supersonic flows, Part I: the normal wire. Exps Fluids 1, 83.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
Spina, E. F., Donovan, J. F. & Smits, A. J. 1991a On the structure of high-Reynolds-number supersonic turbulent boundary layers. J. Fluid Mech. 222, 293–327.Google Scholar
Spina, E. F., Donovan, J. F. & Smits, A. J. 1991b Convection velocity in supersonic turbulent boundary layers. Phys. Fluids A 3, 3124–3126.Google Scholar
Spina, E. F. & Smits, A. J. 1987 Organized structure in a compressible turbulent boundary layer. J. Fluid Mech. 182, 85–109.Google Scholar
Sturek, W. B. & Danberg, J. E. 1972a Supersonic turbulent boundary layer in adverse pressure gradient, Part I: the experiment. AIAA J. 10, 475–480.Google Scholar
Sturek, W. B. & Danberg, J. E. 1972b Supersonic turbulent boundary layer in adverse pressure gradient, Part II: data analysis. AIAA J. 10, 630–635.Google Scholar
Thomann, H. 1968 Effect of streamwise wall curvature on heat transfer in a turbulent boundary layer. J. Fluid Mech. 156, 419.Google Scholar
Van Driest, E. R. 1951 Turbulent boundary layer in compressible fluids. J. Aero. Sci. 128, 283.Google Scholar
Wallace, J. M., Eckelmann, H. & Brodkey, R. S. 1972 The wall region in turbulent shear flow. J. Fluid Mech. 54, 39.Google Scholar