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Numerical simulation of fully-developed compressible flows over wavy surfaces

Numerical simulation of fully-developed compressible flows over wavy surfaces
Numerical simulation of fully-developed compressible flows over wavy surfaces
Rough surfaces are common on high-speed vehicles, for example on heat shields, but compressibility is
not usually taken into account in the flow modelling other than through the mean density. In the present
study, supersonic fully-developed turbulent rough wall channel flows are simulated using direct numerical
simulation to investigate whether strong compressibility effects significantly alter the mean flow and
turbulence properties across the channel. The simulations were run for three different Mach numbers
M = 0.3, 1.5 and 3.0 over a range of wall amplitude-to-wavelength ratios from 0.01 to 0.08, corresponding
to transitionally and fully rough cases respectively. The velocity deficit values are found to decrease with
increasing Mach number. It is also found that at Mach 3.0 significant differences occur in the mean flow
and turbulence statistics throughout the channel and not just in a roughness sublayer. These differences
are found to be due to the presence of strong shock waves created by the peaks of the roughness
elements.
0142-727X
2-15
Tyson, c.j.
4dfb3d55-4c39-48fd-96df-0f4d14734adf
Sandham, N. D.
0024d8cd-c788-4811-a470-57934fbdcf97
Tyson, c.j.
4dfb3d55-4c39-48fd-96df-0f4d14734adf
Sandham, N. D.
0024d8cd-c788-4811-a470-57934fbdcf97

Tyson, c.j. and Sandham, N. D. (2013) Numerical simulation of fully-developed compressible flows over wavy surfaces. International Journal of Heat and Fluid Flow, 41, 2-15. (doi:10.1016/j.ijheatfluidflow.2013.02.006).

Record type: Article

Abstract

Rough surfaces are common on high-speed vehicles, for example on heat shields, but compressibility is
not usually taken into account in the flow modelling other than through the mean density. In the present
study, supersonic fully-developed turbulent rough wall channel flows are simulated using direct numerical
simulation to investigate whether strong compressibility effects significantly alter the mean flow and
turbulence properties across the channel. The simulations were run for three different Mach numbers
M = 0.3, 1.5 and 3.0 over a range of wall amplitude-to-wavelength ratios from 0.01 to 0.08, corresponding
to transitionally and fully rough cases respectively. The velocity deficit values are found to decrease with
increasing Mach number. It is also found that at Mach 3.0 significant differences occur in the mean flow
and turbulence statistics throughout the channel and not just in a roughness sublayer. These differences
are found to be due to the presence of strong shock waves created by the peaks of the roughness
elements.

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Published date: June 2013
Organisations: Aerodynamics & Flight Mechanics Group

Identifiers

Local EPrints ID: 360898
URI: http://eprints.soton.ac.uk/id/eprint/360898
ISSN: 0142-727X
PURE UUID: 4368afa8-f615-4506-ad11-594faf7be4fd
ORCID for N. D. Sandham: ORCID iD orcid.org/0000-0002-5107-0944

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Date deposited: 08 Jan 2014 12:42
Last modified: 21 Nov 2021 02:47

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Contributors

Author: c.j. Tyson
Author: N. D. Sandham ORCID iD

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