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A numerical study of turbulent supersonic isothermal-wall channel flow

Published online by Cambridge University Press:  26 April 2006

G. N. Coleman ,
J. Kim  and
R. D. Moser
G. N. Coleman
Affiliation:
Mechanical, Aerospace, and Nuclear Engineering Department, UCLA, 48-121 Engr. IV, Box 951597, Los Angeles, CA 90095-1597, USA
J. Kim
Affiliation:
Mechanical, Aerospace, and Nuclear Engineering Department, UCLA, 48-121 Engr. IV, Box 951597, Los Angeles, CA 90095-1597, USA
R. D. Moser
Affiliation:
NASA Ames Research Center, Moffett Field, CA 94035-1000, USA Present address:Department of Theoretical and Applied Mechanics, University of Illinois, Urbana, IL 61801 USA.
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Abstract

A study of compressible supersonic turbulent flow in a plane channel with isothermal walls has been performed using direct numerical simulation. Mach numbers, based on the bulk velocity and sound speed at the walls, of 1.5 and 3 are considered; Reynolds numbers, defined in terms of the centreline velocity and channel half-width, are of the order of 3000. Because of the relatively low Reynolds number, all of the relevant scales of motion can be captured, and no subgrid-scale or turbulence model is needed. The isothermal boundary conditions give rise to a flow that is strongly influenced by wall-normal gradients of mean density and temperature. These gradients are found to cause an enhanced streamwise coherence of the near-wall streaks, but not to seriously invalidate Morkovin's hypothesis : the magnitude of fluctuations of total temperature and especially pressure are much less than their mean values, and consequently the dominant compressibility effect is that due to mean property variations. The Van Driest transformation is found to be very successful at both Mach numbers, and when properly scaled, statistics are found to agree well with data from incompressible channel flow results.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 305 , 25 December 1995 , pp. 159 - 183
Copyright
© 1995 Cambridge University Press

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