Journal of Fluid Mechanics



A numerical study of turbulent supersonic isothermal-wall channel flow


G. N.  Coleman a1, J.  Kim a1 and R. D.  Moser a2p1
a1 Mechanical, Aerospace, and Nuclear Engineering Department, UCLA, 48-121 Engr. IV, Box 951597, Los Angeles, CA 90095-1597, USA
a2 NASA Ames Research Center, Moffett Field, CA 94035-1000, USA

Article author query
coleman gn   [Google Scholar] 
kim j   [Google Scholar] 
moser rd   [Google Scholar] 
 

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.

(Published Online April 26 2006)
(Received December 31 1994)
(Revised May 11 1995)


Correspondence:
p1 Present address:Department of Theoretical and Applied Mechanics, University of Illinois, Urbana, IL 61801 USA.


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