Hostname: page-component-78c5997874-v9fdk Total loading time: 0 Render date: 2024-11-14T16:43:45.744Z Has data issue: false hasContentIssue false
  • English
  • Français

An experimental investigation of heat transfer effects on boundary layer separation in supersonic flow

Published online by Cambridge University Press:  28 March 2006

G. E. Gadd
G. E. Gadd
Affiliation:
Aerodynamics Division, National Physical Laboratory, Teddington
Get access Rights & Permissions [Opens in a new window]

Abstract

Experiments have been done on the effects of heat transfer on wall-pressure distributions through separated regions with both laminar and turbulent boundary layers at a free-stream Mach number of about 3. The temperature of the flat plate on which the boundary layer was formed could be varied from about − 35° C to + 75° C. According to theory, this variation should have produced appreciable alterations at a laminar separation point in either the pressure or the pressure gradient, but no sign of this appeared in the overall pressure distributions, which, for laminar layers, remained unaffected by wall temperature. A possible explanation is given for this apparent discrepancy between theory and experiment. With turbulent layers, the variations in wall temperature did produce small changes in the pressure distributions. However, for most practical purposes such changes could be ignored. Hence the convenient conclusion is suggested that in supersonic separating flow with either a laminar or a turbulent boundary layer the pressure distributions are not significantly affected by moderate variations in wall temperature.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 2 , Issue 2 , March 1957 , pp. 105 - 122
Copyright
© 1957 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

Bradfield, W. S., de Coursin, D. G. & Blumer, C. B. 1954 The effects of leading edge bluntness on a laminar supersonic boundary layer, J. Aero. Sci. 21, 373.
Cohen, C. B. & Reshotko, E. 1955a Similar solutions for the compressible laminar boundary layer with heat transfer and pressure gradient, Nat. Adv. Comm. Aero., Wash., Tech. Note no. 3325.Google Scholar
Cohen, C. B. & Reshotko, E. 1955b The compressible laminar boundary layer with heat transfer and arbitrary pressure gradient, Nat. Adv. Comm. Aero., Wash., Tech. Note no. 3326.Google Scholar
Gadd, G. E. 1952 The numerical integration of the laminar compressible boundary layer equations, with special reference to the position of separation when the wall is cooled, Aero. Res. Counc., Lond., Rep. no. 15,101.Google Scholar
Gadd, G. E. 1956a A theoretical investigation of the effects of Mach number, Reynolds number, wall temperature and surface curvature on laminar separation in supersonic flow, Aero. Res. Counc., Lond., Rep. no. 18,494.Google Scholar
Gadd, G. E. 1956b A review of theoretical work relevant to the problem of heat transfer effects on laminar separation, Aero. Res. Counc., Lond., Rep. no. 18,495.Google Scholar
Gadd, G. E., Holder, D. W. & Regan, J. D. 1954 An experimental investigation of the interaction between shock waves and boundary layers, Proc. Roy. Soc. A, 226, 227.
Howarth, L. (Ed.). 1953 Modern Developments in Fluid Dynamics. High Speed Flow. Vol. 1. Oxford: Clarendon Press.
Illingworth, C. R. 1954 The effect of heat transfer on the separation of a compressible laminar boundary layer, Quart. J. Mech. Appl. Math. 7, 8.
Morduchow, M. & Grape, R. G. 1955 Separation, stability, and other properties of compressible laminar boundary layer with pressure gradient and heat transfer, Nat. Adv. Comm. Aero., Wash., Tech. Note no. 3296.Google Scholar
Taylor, G. I. 1938 Measurements with a half Pitot tube, Proc. Roy. Soc. A, 166, 476.