Skip to main content
Article thumbnail
Location of Repository

Implicit large-eddy simulation of low-speed separated flows using high-resolution methods

By Marco Hahn

Abstract

Most flows of practical importance are governed by viscous near-wall phenomena leading to separation and subsequent transition to a turbulent state. This type of problem currently poses one of the greatest challenges for computational methods because its characteristics covers a wide range of physical processes that often place contradictory requirements on the numerics employed. This thesis seeks to investigate the physics of complex, separated flows pertinent to aeronautical engineering and to assess the performance of variants of the Implicit Large-Eddy Simulation approach in predicting this type of problem realistically. For this purpose, different numerical solution strategies based on high-resolution methods, distinguished by their order of accuracy, are used in precursor simulations and one selected approach is applied to a fully three-dimensional wing flow. In order to isolate the development from laminar to turbulent flow after separation has occurred, the prototype Taylor-Green Vortex is considered. Here, the behaviour of the numerical schemes during the linear, non-linear and fully turbulent stages in the flow evolution is tested for different grid sizes. It is found that the resolution power and the likelihood of symmetry breaking is increasing with the order of accuracy of the numerical method. These two properties allow the flow to develop more realistically on coarse grids if higher order schemes are employed. In the next step, flow separation from a gently curved surface is included. The fundamental study of a statistically two-dimensional channel flow with hill-type constrictions demonstrates the basic applicability of ILES to problems featuring massive separation. Without specific wall-treatment, high-resolution methods can improve prediction of the detachment location when compared to classical Large-Eddy Simulations. Finally, an ILES simulation of three-dimensional flow over a swept wing geometry at moderate angle of incidence is presented. The results are in excellent agreement with experiment in the fully separated and turbulent region and they are more accurate than a classical hybrid RANS/LES approach, using a grid twice the size, over the majority of the wing. This outcome will probably settle the dispute that has erupted in the past over the applicability of ILES to complex, wall-bounded flows

Publisher: Cranfield University
Year: 2008
OAI identifier: oai:dspace.lib.cranfield.ac.uk:1826/2633
Provided by: Cranfield CERES

Suggested articles

Citations

  1. (2003). Application of MILES to Rayleigh-Taylor and RichtmyerMeshkov mixing. doi
  2. (1998). Hybrid upwind methods for the simulation of unsteady shock-wave diffraction over a cylinder. Computer Methods in Applied Mechanics and Engineering, doi
  3. (1970). Le tunnelhydrodynamiqueau servicedel’industrie.
  4. (2004). Near-Surface Topology and Flow Structure on a Delta Wing. doi
  5. (1991). Three-dimensional numerical simulation of turbulent mixing by Rayleigh-Taylor instability. doi

To submit an update or takedown request for this paper, please submit an Update/Correction/Removal Request.