Future Directions in Computational Fluid Dynamics

Witherden, Freddie D.; Jameson, Antony

doi:10.2514/6.2017-3791

Cited by 37 publications

(27 citation statements)

References 51 publications

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“…Table (1): The location of the primary vortex and the two side vortices for Re=100,400& 1000 using the MRT LBM compared to published results (Ref. [14,15,[29][30][31]).…”

Section: Numerical Resultsmentioning

confidence: 99%

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Simulation of the Lid-Driven Cavity Flow at Reynolds Numbers Between 100 and 1000 Using the Multi-Relaxation-Time Lattice Boltzmann Method

Boraey

2017

Mugla Journal of Science and Technology

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The Multi-Relaxation-Time Lattice Boltzmann Method (MRT LBM) is used to numerically simulate the steady viscous incompressible flow in a lid-driven cavity. The simulations are performed for a range of Reynolds numbers between 100 and 1000. The simulation results include the flow streamlines which clearly show the location of the primary main vortex and the two side vortices, the horizontal and vertical velocity component profiles at different sections inside the cavity and the location of the vortices centers. The numerical results are compared against published results and show a perfect agreement. The simulation results are given for a range of Reynolds numbers not reported in the published literature. The presented results can be used for benchmarking other numerical methods in the reported range of the Reynolds number. The MRT LBM is used because it has the advantages of being an explicit method, can deal easily with complex boundaries and is highly parallelizable.

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“…Table (1): The location of the primary vortex and the two side vortices for Re=100,400& 1000 using the MRT LBM compared to published results (Ref. [14,15,[29][30][31]).…”

Section: Numerical Resultsmentioning

confidence: 99%

“…Computational fluid dynamics (CFD) techniques have changed and varied dramatically in the past few years [1]. The reason for this is the diversity in the applications of the CFD [2][3][4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Simulation of the Lid-Driven Cavity Flow at Reynolds Numbers Between 100 and 1000 Using the Multi-Relaxation-Time Lattice Boltzmann Method

Boraey

2017

Mugla Journal of Science and Technology

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“…In the early 1940s, finite difference numerical methods were used to solve practical partial differential equations at Los Alamos National Laboratory by using the first electronic computer . Due to the limits of available computing resources in the 1970s, it was impossible to solve the three‐dimensional Euler equations over complete aircraft configurations, but to solve small perturbation equations or fully potential flow models . Along with the development of High‐Performance Computing (HPC) with the capability of processing a huge amount of data and high‐speed intercommunicating network, the Reynolds Averaged Navier‐Stokes (RANS) simulations were applied to three‐dimensional viscous flows in the 1990s.…”

Section: Introductionmentioning

confidence: 99%

A large‐scale parallel hybrid grid generation technique for realistic complex geometry

Zhao

Zhang

et al. 2020

Numerical Methods in Fluids

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Summary High‐Performance Computing (HPC) systems and Computational Fluid Dynamics (CFD) have made significant progress in recent years; however, as the basis of the large‐scale parallel computing, the massive grid generation of billions of cells has become a bottleneck problem. In this study, a parallel grid generation technique is proposed to generate large‐scale mixed grids with arbitrary cell types and scales. The basic idea of our method is analogous to the global mesh refinement technique. An initial coarse grid with arbitrary cell types is regarded as a background mesh which is partitioned into subzones, and subzones are assigned onto different CPU cores. After the cells and faces in each subzone are split, the inserted new points of the solid wall are projected onto the original CAD entities to preserve the geometry accurately. Finally, the tangled cells caused by the projection in the boundary layer are untangled by a local Radial Basis Function mesh deformation technique. Furthermore, a parallel partition approach and an efficient wall distance computing technique for massive grids are developed also to shorten the preprocessing time. The tests show that the preprocessing efficiency has been increased by two or three orders compared with traditional methods. Billions of grids are generated for the AIAA JSM high‐lift model and the Chinese CHN‐T1 transport model to test the ability of the parallel grid generation technique. The maximum scale up to 19 billion mixed elements is generated using 16 384 CPU cores in parallel, and the mesh quality is acceptable for CFD simulations.

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“…The main challenge today in Computational Fluid Dynamics (CFD) for aerodynamics is to reliably predict turbulent-separated flows Witherden & Jameson (2017), Slotnick et al (2014), specifically for a complete air vehicle. This is our focus in this paper.…”

Section: Introductionmentioning

confidence: 99%

“…Boundary layer models require tailored boundary layer meshes, which are expensive in terms of both mesh density and manual work. Witherden and Jameson in Witherden & Jameson (2017) state that "as a community we are still far away from LES of a complete air vehicle".…”

Section: Introductionmentioning

confidence: 99%

Time-Resolved Adaptive Direct FEM Simulation of High-Lift Aircraft Configurations

Jansson

Krishnasamy

Leoni

et al. 2018

Numerical Simulation of the Aerodynamics of High-Lift Configurations

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We present an adaptive finite element method for time-resolved simulation of aerodynamics without any turbulence model parameters, which is applied to a benchmark problem from the HiLiftPW-3 workshop to compute the flow past a JAXA Standard Model (JSM) aircraft model at realistic Reynolds number. The mesh is automatically constructed by the method as part of an adaptive algorithm based on a posteriori error estimation using adjoint techniques. No explicit turbulence model is used, and the effect of unresolved turbulent boundary layers is modeled by a simple parametrization of the wall shear stress in terms of a skin friction. In the case of very high Reynolds numbers we approximate the small skin friction by zero skin friction, corresponding to a free slip boundary condition, which results in a computational model without any model parameter to be tuned, and without the need for costly boundary layer resolution. We introduce a numerical tripping noise term to act as a seed for growth of perturbations, the results support that this triggers the correct physical separation at stall, and has no significant effect pre-stall. We show that the methodology quantitavely and qualitatively captures the main features of the JSM experiment-aerodynamic forces and the stall mechanism-with a much coarser mesh resolution and lower computational cost than the state of the art methods in the field, with convergence under mesh refinement by the adaptive method. Thus, the simulation methodology appears to be a possible answer to the challenge of reliably predicting turbulent-separated flows for a complete air vehicle.

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Future Directions in Computational Fluid Dynamics

Cited by 37 publications

References 51 publications

Simulation of the Lid-Driven Cavity Flow at Reynolds Numbers Between 100 and 1000 Using the Multi-Relaxation-Time Lattice Boltzmann Method

Simulation of the Lid-Driven Cavity Flow at Reynolds Numbers Between 100 and 1000 Using the Multi-Relaxation-Time Lattice Boltzmann Method

A large‐scale parallel hybrid grid generation technique for realistic complex geometry

Time-Resolved Adaptive Direct FEM Simulation of High-Lift Aircraft Configurations

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