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Title of Journal: Theor Comput Fluid Dyn

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Abbravation: Theoretical and Computational Fluid Dynamics

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Springer-Verlag

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DOI

10.1016/1043-6618(92)90825-V

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1432-2250

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Hypersonic viscous flow over large roughness eleme

Authors: ChauLyan Chang Meelan M Choudhari
Publish Date: 2010/04/20
Volume: 25, Issue: 1-4, Pages: 85-104
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Abstract

Viscous flow over discrete or distributed surface roughness has great implications for hypersonic flight due to aerothermodynamic considerations related to laminar–turbulent transition Current prediction capability is greatly hampered by the limited knowledge base for such flows To help fill that gap numerical computations are used to investigate the intricate flow physics involved An unstructured mesh compressible Navier–Stokes code based on the space–time conservation element solution element CESE method is used to perform timeaccurate Navier–Stokes calculations for two roughness shapes investigated in wind tunnel experiments at NASA Langley Research Center It was found through 2D parametric study that at subcritical Reynolds numbers spontaneous absolute instability accompanying by sustained vortex shedding downstream of the roughness is likely to take place at subsonic freestream conditions On the other hand convective instability may be the dominant mechanism for supersonic boundary layers Threedimensional calculations for both a rectangular and a cylindrical roughness element at postshock Mach numbers of 41 and 65 also confirm that no selfsustained vortex generation from the top face of the roughness is observed despite the presence of flow unsteadiness for the smaller postshock Mach number case

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