摘要:

Large Eddy Simulation (LES) of the decay of isotropic turbulence and of channel flow has been performed using an explicit second-order unstructured grid algorithm for tetrahedral cells. The algorithm solves for cell-averaged values using the finite volume form of the unsteady compressible Jittered Navier-Stokes equations. The inviscid fluxes are obtained from Godunov's exact Riemann solver. Reconstruction of the flow variables to the left and right sides of each face is performed using least squares or Frink's method. The viscous fluxes and heat transfer are obtained by application of Gauss' theorem. LES of the decay of nearly incompressible isotropic turbulence has been performed using two models for the SGS stresses: the Monotone Integrated Large Eddy Simulation (MILES) approach, wherein the inherent numerical dissipation models the sub-grid scale (SGS) dissipation, and the Smagorinsky SGS model. The results using the MILES approach with least squares reconstruction show good agreement with incompressible experimental data. The contribution of the Smagorinsky SGS model is negligible. LES of turbulent channel flow was performed at a Reynolds number (based on channel height and bulk velocity) of 5600 and Mach number of 0.5 (at which compressibility effects are minimal) using Smagorinsky's SGS model with van Driest damping. The results show good agreement with experimental data and direct numerical simulations for incompressible channel flow. The SGS eddy viscosity is less than 10% of the molecular viscosity, and therefore the LES is effectively MILES with molecular viscosity.

ISSN:1061-8562    

DOI:10.1080/10618560008940904

出版商:Taylor & Francis Group    

年代:2000

数据来源: Taylor

摘要:

A Large Eddy Simulation (LES) of turbulent flow over an airfoil near stall is performed. Results of the LES are compared with those of Reynolds-Averaged Navier-Stokes (RANS) simulations using two well-known turbulence models, namely the Baldwin-Lomax model and the Spalart-Allmaras model. The subgrid scale model used for the LES is the filtered structure function model. All simulations are performed using the same structured multi-block code. In order to reduce the CPU time, an implicit time stepping method is used for the LES. The purpose of this study is to show the possibilities and limitations of LES of complex flows associated with aeronautical applications using state of the art simulation techniques. Typical flow features are captured by the LES such as the adverse-pressure gradient and flow retardation. Visualization of instantaneous flow fields shows the typical streaky structures in the near-wall region.

ISSN:1061-8562    

DOI:10.1080/10618560008940905

出版商:Taylor & Francis Group    

年代:2000

数据来源: Taylor

摘要:

In this paper the performance of different free stream boundary conditions has been investigated. By performing two dimensional free jet calculations, a test case for which an analytical solution is available, it has been shown that boundary conditions in which the pressure is prescribed perform significantly better than boundary conditions in which the velocity is prescribed. Furthermore, it has been shown that pressure boundary conditions allow for much smaller computational domains than velocity (free-slip) boundary conditions.

ISSN:1061-8562    

DOI:10.1080/10618560008940906

出版商:Taylor & Francis Group    

年代:2000

数据来源: Taylor

摘要:

A Finite-Volume scheme which enables computing fast transient single phase and two phase flows in variable cross section ducts is presented. The physical modelling relies on the Homogeneous Relaxation Model. The theoretical framework is briefly presented, together with the main ideas of a new approximate Riemann solver. Numerical results confirm the suitability of the present approach.

ISSN:1061-8562    

DOI:10.1080/10618560008940907

出版商:Taylor & Francis Group    

年代:2000

数据来源: Taylor

摘要:

The shape optimization problem governed by the Euler equations is posed in a fixed reference plane. The boundary control is exerted by a parametric mapping from the physical plane to the reference fixed plane. The adjoint equations are derived in such fixed plane. By using this approach remeshing is unnecessary; furthermore, as in many practical applications the parametric mapping can be easily differentiated, the computation of mesh sensitivities is avoided.

ISSN:1061-8562    

DOI:10.1080/10618560008940908

出版商:Taylor & Francis Group    

年代:2000

数据来源: Taylor