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Turbulence Heat and Mass Transfer 6. Proceedings of the Sixth International Symposium On Turbulence Heat and Mass Transfer
September, 14-18, 2009, Rome, Italy

DOI: 10.1615/ICHMT.2009.TurbulHeatMassTransf


ISBN Print: 978-1-56700-262-1

ISSN: 2377-2816

DNS of a spatially developing, supersonic turbulent boundary layer flow over a cooled wall

page 12
DOI: 10.1615/ICHMT.2009.TurbulHeatMassTransf.640
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要約

Some results from the direct numerical simulation of a spatially developing turbulent boundary layer flow at a free-stream Mach number of 2.25 along a cooled wall (Tw/Taw < 1) are presented. The effect of wall-temperature variation can have a large effect on the turbulence dynamics of a wide variety of aeronautical and industrially relevant flows. Engineering flows ranging from turbine blade cooling at or near transonic speeds to nozzle flows at high supersonic or hypersonic velocities provide ample motivation for investigating such isothermal conditions. The mean and fluctuating turbulent statistics presented here primarily focus on comparisons with the same Mach number developing flow field under adiabatic wall conditions.

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