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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
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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

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