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Receptivity of a hypersonic boundary layer over a flat plate with a porous coating

Published online by Cambridge University Press:  25 April 2008

I. V. EGOROV ,
A. V. FEDOROV  and
V. G. SOUDAKOV
I. V. EGOROV
Affiliation:
Department of Aeromechanics and Flight Engineering, Moscow Institute of Physics and Technology, Zhukovsky, 140180, Russia
A. V. FEDOROV
Affiliation:
Department of Aeromechanics and Flight Engineering, Moscow Institute of Physics and Technology, Zhukovsky, 140180, Russia
V. G. SOUDAKOV
Affiliation:
Department of Aeromechanics and Flight Engineering, Moscow Institute of Physics and Technology, Zhukovsky, 140180, Russia
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Abstract

Two-dimensional direct numerical simulation (DNS) of receptivity to acoustic disturbances radiating onto a flat plate with a sharp leading edge in the Mach 6 free stream is carried out. Numerical data obtained for fast and slow acoustic waves of zero angle of incidence are consistent with the asymptotic theory. Numerical experiments with acoustic waves of non-zero angles of incidence reveal new features of the disturbance field near the plate leading edge. The shock wave, which is formed near the leading edge owing to viscous–inviscid interaction, produces a profound effect on the acoustic near field and excitation of boundary-layer modes. DNS of the porous coating effect on stability and receptivity of the hypersonic boundary layer is carried out. A porous coating of regular porosity (equally spaced cylindrical blind micro-holes) effectively diminishes the second-mode growth rate in accordance with the predictions of linear stability theory, while weakly affecting acoustic waves. The coating end effects, associated with junctures between solid and porous surfaces, are investigated.

Type
Papers
Information
Journal of Fluid Mechanics , Volume 601 , 25 April 2008 , pp. 165 - 187
Copyright
Copyright © Cambridge University Press 2008

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