Synthetic turbulence generation for high-order scale-resolving simulations on unstructured grids
File(s)
Accepted version
Author(s)
Giangaspero, Giorgio
Witherden, Freddie
Vincent, Peter
Type
Journal Article
Abstract
An extended version of the synthetic eddy method for generation of synthetic turbulence has been developed via a
source term formulation and implemented in the open-source cross-platform solver PyFR. The method caters for the
full space-dependent anisotropy of the target turbulent length scales, and it is agnostic of the space and time
discretization of the underlying solver, which can be incompressible or compressible. Moreover, the method does
not require each solution point to communicate with nearest neighbors; thus, it is well suited for modern, massively
parallel, high-order unstructured codes which support mixed and possibly curved elements. The method has been
applied to two test cases: incompressible plane channel flow at Reτ 180 and compressible flow over an SD7003
aerofoil at Re 66;000, Ma 0.2, and α 4 deg. The channel flow case was run on three topologically different
meshes composed of hexahedra, prisms, and a combination of prisms and tetrahedra, respectively. Almost identical
results have been obtained on the three meshes. Results also show that taking into account the anisotropy of the
turbulent length scales can reduce the development length. For the SD7003 aerofoil case, the injection of synthetic
turbulence improves agreement between numerical and experimental results.
source term formulation and implemented in the open-source cross-platform solver PyFR. The method caters for the
full space-dependent anisotropy of the target turbulent length scales, and it is agnostic of the space and time
discretization of the underlying solver, which can be incompressible or compressible. Moreover, the method does
not require each solution point to communicate with nearest neighbors; thus, it is well suited for modern, massively
parallel, high-order unstructured codes which support mixed and possibly curved elements. The method has been
applied to two test cases: incompressible plane channel flow at Reτ 180 and compressible flow over an SD7003
aerofoil at Re 66;000, Ma 0.2, and α 4 deg. The channel flow case was run on three topologically different
meshes composed of hexahedra, prisms, and a combination of prisms and tetrahedra, respectively. Almost identical
results have been obtained on the three meshes. Results also show that taking into account the anisotropy of the
turbulent length scales can reduce the development length. For the SD7003 aerofoil case, the injection of synthetic
turbulence improves agreement between numerical and experimental results.
Date Issued
2022-02-01
Date Acceptance
2021-08-21
Citation
AIAA Journal: devoted to aerospace research and development, 2022, 60 (2), pp.1032-1051
ISSN
0001-1452
Publisher
American Institute of Aeronautics and Astronautics
Start Page
1032
End Page
1051
Journal / Book Title
AIAA Journal: devoted to aerospace research and development
Volume
60
Issue
2
Copyright Statement
Copyright © 2021 by the
authors. Published by the American Institute of Aeronautics and Astronautics,
Inc., with permission. All requests for copying and permission to reprint
should be submitted to CCC at www.copyright.com; employ the eISSN
1533-385X to initiate your request. See also AIAA Rights and Permissions
www.aiaa.org/randp
authors. Published by the American Institute of Aeronautics and Astronautics,
Inc., with permission. All requests for copying and permission to reprint
should be submitted to CCC at www.copyright.com; employ the eISSN
1533-385X to initiate your request. See also AIAA Rights and Permissions
www.aiaa.org/randp
Sponsor
Engineering & Physical Science Research Council (EPSRC)
Identifier
http://gateway.webofknowledge.com/gateway/Gateway.cgi?GWVersion=2&SrcApp=PARTNER_APP&SrcAuth=LinksAMR&KeyUT=WOS:000719737600001&DestLinkType=FullRecord&DestApp=ALL_WOS&UsrCustomerID=1ba7043ffcc86c417c072aa74d649202
Grant Number
EP/R030340/1
Subjects
Science & Technology
Technology
Engineering, Aerospace
Engineering
Isotropic Turbulence
Unstructured Grid
Incompressible Flow
Aerofoil
Boundary Layer Transition
Direct Numerical Simulation
Reynolds Averaged Navier Stokes
Power Spectral Density
Finite Element Scheme
Kinematic Viscosity
DIRECT NUMERICAL-SIMULATION
LAMINAR SEPARATION-BUBBLES
LARGE-EDDY SIMULATIONS
INFLOW CONDITIONS
CHANNEL FLOW
BOUNDARY-LAYER
Publication Status
Published
Date Publish Online
2021-11-05