Hostname: page-component-cd9895bd7-8ctnn Total loading time: 0 Render date: 2024-12-18T21:48:58.017Z Has data issue: false hasContentIssue false
  • English
  • Français

An experiment on the adiabatic compressible turbulent boundary layer in adverse and favourable pressure gradients

Published online by Cambridge University Press:  29 March 2006

J. E. Lewis ,
R. L. Gran  and
T. Kubota
J. E. Lewis
Affiliation:
TRW Systems Group, Redondo Beach, California
R. L. Gran
Affiliation:
TRW Systems Group, Redondo Beach, California
T. Kubota
Affiliation:
California Institute of Technology, Pasadena, California
Get access Rights & Permissions [Opens in a new window]

Abstract

A wind-tunnel model was developed to study the two-dimensional turbulent boundary layer in adverse and favourable pressure gradients with out the effects of streamwise surface curvature. Experiments were performed at Mach 4 with an adiabatic wall, and mean flow measurements within the boundary layer were obtained. The data, when viewed in the velocity transformation suggested by Van Driest, show good general agreement with the composite boundary-layer profile developed for the low-speed turbulent boundary layer. Moreover, the pressure gradient parameter suggested by Alber & Coats was found to correlate the data with low-speed results.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 51 , Issue 4 , 22 February 1972 , pp. 657 - 672
Copyright
© 1972 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

Abarbanel, S. S., Hapkinen, R. J. & Trilling, L. 1959 Use o f a Stanton tube for skinfriction measurements. N.A.S.A. Memo. 2-17-59W.
Alber, I. E. & Coats, D. E. 1969 Analytical Inwestigation of Equilibrium and Non-Equilibrium Compressible Turbulent Boundary Layers. A.I.A.A. Paper, 69–689.
Baronti, P. O. & Libby, P. A. 1966 Velocity profiles in turbulent compressible boundary layers. A.I.A.A.J. 4, 193–201.Google Scholar
Bradshaw, P. & Ferriss, D. H. 1965 The response of a retarded equilibrium turbulent boundary layer to the sudden removal of pressure gradient. Nut. Phys. Lab. Aero. Rep. 1145.
Bradshaw, P. & Gregory, M. A. 1961 The determination of local turbulent skin friction from observations in the viscous sublayer. Aero. Res. Counc. R. & M. 3202.
Brott, D. L., Yanta, W. J. & Lee, R. E. 1968 An experimental investigation of the surface Pitot probe including effects of heat transfer and compressibility. Nav. Ord. Lab. Tech. Rep. 68–151.
Clauser, F. H. 1956 The turbulent boundary layer. Adwanc. AppZ. Mech. 4, 1–51.Google Scholar
Coles, D. E. 1953 Measurements in the boundary layer on a smooth flat plate in supersonic flow, 1. The problem of the turbulent boundary layer. Jet Propulsion Lab. Rep. 20–69.
Coles, D. E. 1956 The law of the wake in the turbulent boundary layer. J. Fluid Mech. 1, 191–226.Google Scholar
Coles, D. E. 1962 The turbulent boundary layer in a compressible fluid. Rand. Corporation, Santa Monica, California, Rep. R-403-Pr.
Coles, D. E. & Hirst, E. A. 1969 Proceedings Computation of Turbulent Boundary Layers, 1968 AFOSR-IFP-Stanford Conference, vol. II. Thermosciences Division, Stanford University, California.
Herring, H. J. & Norbury, J. F. 1967 Some experiments on equilibrium turbulent boundary layers in favourable pressure gradients. J. Fluid Mech. 27, 541–549.Google Scholar
Hool, J. N. 1956 Measurements of skin friction using surface tubes. J. Aircraft Eng. 28, 52–53.Google Scholar
Hopkins, E. J. & Inouye, M. 1971 An evaluation of theories for predicting turbulent skin friction and heat transfer on flat plates a t supersonic and hypersonic Mach numbers. A.I.A.A.J. 9, 993–1003.Google Scholar
Hopkins, E. J. & Keener, E. R. 1966 Study of surface Pitots for measuring turbulent skin friction at supersonic Mach numbers - adiabatic wall. N.A.S.A. Tech. Note D–3478.
Lewis, J. E., Kubota, T. & Webb, W. H. 1970 Transformation theory for the adiabatic compressible turbulent boundary layer with pressure gradient. A.I.A.A.J. 8, 1644–1650.Google Scholar
Maise, G. & McDonald, H. 1967 Mixing Length and KinematicEddy Viscosity in a Compressible Boundary Layer. A.I.A.A. 5th Aerospace Sciences Meeting.
Mellor, G. L. & Gibson, D. M. 1966 Equilibrium turbulent boundary layers. J. Fluid Mech. 24, 225–253.Google Scholar
Smith, K. G., Gaudet, L. & Winter, K. G. 1964 The use of surface Pitot tubes as skin-friction meters at supersonic speeds. Aeron. Res. Counc. R. & M. 3351.
Stratford, B. S. 1959 An experimental flow with zero skin friction throughout its region of pressure rise. J. Fluid Mech. 5, 17–35.Google Scholar
Van Driest, E. R. (1951). The turbulent boundary layer in compressible fluids. J. Aero. Sci. 18, 145–160.Google Scholar