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Transonic shockwave/turbulent boundary layer interactions on a porous surface

Published online by Cambridge University Press:  04 July 2016

N. Chokani  and
L. C. Squire
N. Chokani
Affiliation:
Department of Engineering, University of Cambridge
L. C. Squire
Affiliation:
Department of Engineering, University of Cambridge
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Abstract

Transonic shockwave/turbulent boundary layer interactions on a porous surface above a closed plenum chamber have been studied experimentally in the choked flow of a windtunnel test-section. The equivalent freestream Mach number is 0.76 and results were obtained for three shock strengths. Without the porous surface the Mach numbers ahead of the shock were 1.13, 1.18 and 1.26. The respective shock Mach numbers with the porous surface were 1.10, 1.11 and 1.19. Laser holographic interferometry results are used to measure the density flowfield and examine the nature of the interaction. These results show that the interaction on the porous surface is modified by a thin shear layer adjacent to the surface and the weakening of the Shockwave is attributed to this. The interaction was also studied by solving the two-dimensional Reynolds-averaged Navier-Stokes equations together with the two-layer algebraic eddy-viscosity model of Baldwin-Lomax modified with appropriate corrections for surface transpiration. The computed results show excellent agreement with the experimental data. The examination of these numerical results shows that the surface transpiration occurs at a low subsonic velocity and suggests that the effect of the transpiration through the porous surface on the interaction may be optimised.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 97 , Issue 965 , May 1993 , pp. 163 - 170
Copyright
Copyright © Royal Aeronautical Society 1993 

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Footnotes

*

Department of Mechanical and Aerospace Engineering, North Carolina State University, Raleigh, USA.

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