Hostname: page-component-76fb5796d-r6qrq Total loading time: 0 Render date: 2024-04-27T19:12:46.296Z Has data issue: false hasContentIssue false
  • English
  • Français

On the integral properties of separated laminar boundary layers

Published online by Cambridge University Press:  29 March 2006

A. A. Sfeir
A. A. Sfeir
Affiliation:
Department of Mechanical Engineering, American University of Beirut
Get access Rights & Permissions [Opens in a new window]

Abstract

Detailed measurements of the flow over a compression corner were taken using hot-wire probes. The experiments were performed in supersonic flow (M = 2·64) under adiabatic wall conditions. The incompressible analogues of the boundary-layer profiles were obtained and their integral characteristics and shape factors correlated. Comparison with the self-similar profiles used by Lees & Reeves (1964) to describe interaction problems showed some similarities between the shape factors, but the measured negative shears in the separated bubble proved to be much less.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 60 , Issue 1 , 21 August 1973 , pp. 97 - 104
Copyright
© 1973 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

Chapman, D. R., Kuehn, D. M. & Larson, K. L. 1958 Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition. N.A.C.A. Rep. no. 1356.Google Scholar
Cohen, C. B. & Reshotko, E. 1956 Similar solutions for the compressible laminar boundary layer with heat transfer and pressure gradient. N.A.C.A. Rep. no. 1293.Google Scholar
Curle, N. 1961 The effect of heat transfer on laminar boundary layer separation in supersonic flow. Aero. Quart. 12, 309–336.Google Scholar
Dewey, C. F. 1965 A correlation of convective heat transfer and recovery temperature data for cylinders in compressible flow, J. Heat & Mass Transfer, 8, 245–252.Google Scholar
Hankey, W. L. & Cross, E. J. 1967 Approximate closed-form solution for supersonic laminar separated flows. A.I.A.A. J. 5, 651–654.Google Scholar
Holden, M. S. 1970 Boundary-layer displacement and leading edge bluntness effects on attached and separated laminar boundary layers in a compression corner. Part 1. Theoretical study. A.I.A.A. J. 8, 2179–2188.Google Scholar
Kovasznay, L. S. G. 1953 Hot wire methods. High Speed Aerodynamics and Jet Propulsion Princeton Ser. 9, 219–241.Google Scholar
Lees, L. & Reeves, B. L. 1964 Supersonic separated and reattaching supersonic flows. A.I.A.A. J. 2, 1907–1920.Google Scholar
Lewis, J. E. 1967 Experimental investigation of supersonic two-dimensional boundarylayer separation in a compression corner with and without cooling. Ph.D. thesis, California Institute of Technology.
Lu, T. A. 1970 Theoretical investigation of supersonic laminar separation in a concave corner. University of California, Berkeley Rep. AS-70–2.Google Scholar
Sfeir, A. A. 1969 Supersonic laminar boundary layer separation near a compression corner. University of California, Berkeley Rep. AS-69–6.Google Scholar
Siriex, M., Mirande, J. & Delery, J. 1966 Experiences fondamentales sur le recollement turbulent d'un jet supersonique. AGARD Separated Flows, part 1, pp. 342–353.Google Scholar
Stewartson, K. 1954 Further solutions of the Falkner-Skan equation. Proc. Camb. Phil. Soc. 50, 454–465.Google Scholar
Stewartson, K. & Williams, P. G. 1969 Self-induced separation. Proc. Roy. Soc. A 312, 81–206.Google Scholar
Sutton, W. G. L. 1937 An approximate solution of the boundary-layer equation for a flat plate. Phil. Mag. 23, 1146–1152.Google Scholar
Tani, I. 1954 On the approximated solution of the laminar boundary layer equations. J. Aerospace Sci. 21, 487–504.Google Scholar
Thwaites, B. 1949 Approximate calculation of the laminar boundary layer. Aero. Quart. 1, 245.Google Scholar