Unstructured-Mesh Discretizations and Solvers for Computational Aerodynamics

Mavriplis, Dimitri J.

doi:10.2514/1.34681

Cited by 79 publications

(61 citation statements)

References 75 publications

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“…Unstructured mesh methods for computational fluid dynamics have been under development for over 25 years [8]. The original attraction of this approach was based on the success achieved in handling complex geometries, as demonstrated through finite-element-based approaches, mainly in the field of structural analysis.…”

Section: Numerical Analysismentioning

confidence: 99%

“…The original attraction of this approach was based on the success achieved in handling complex geometries, as demonstrated through finite-element-based approaches, mainly in the field of structural analysis. In addition to the flexibility in dealing with complex geometries, the ability to easily incorporate adaptive mesh refinement (AMR) strategies also became one of the often quoted advantages of the unstructured mesh approach [8].…”

Section: Numerical Analysismentioning

confidence: 99%

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Grid Discretization Study for the Efficient Aerodynamic Analysis of the Very Light Aircraft (VLA) Configuration

Sitio¹,

Kim²,

Lee³

2013

International Journal of Aeronautical and Space Sciences

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In this research the development of unstructured grid discretization solution techniques is presented. The purpose is to describe such a conservative discretization scheme applied for experimental validation work. The objective of this paper is to better establish the effects of mesh generation techniques on velocity fields and particle deposition patterns to determine the optimal aerodynamic characteristics.In order to achieve the objective, the mesh surface discretization approaches used the VLA prototype manufacturing tolerance zone of the outer surface. There were 3 schemes for this discretization study implementation. They are solver validation, grid convergence study and surface tolerance study.A solver validation work was implemented for the simple 2D and 3D model to get the optimum solver for the VLA model. A grid convergence study was also conducted with a different growth factor and cell spacing, the amount of mesh can be controlled. With several amount of mesh we can get the converged amount of mesh compared to experimental data. The density around surface model can be calculated by controlling the number of element in every important and sensitive surface area of the model.The solver validation work result provided the optimum solver to employ in the VLA model analysis calculation. The convergence study approach result indicated that the aerodynamic trend characteristic was captured smooth enough compared with the experimental data. During the surface tolerance scheme, it could catch the aerodynamics data of the experiment data. The discretization studies made the validation work more efficient way to achieve the purpose of this paper.

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Section: Numerical Analysismentioning

confidence: 99%

Section: Numerical Analysismentioning

confidence: 99%

Grid Discretization Study for the Efficient Aerodynamic Analysis of the Very Light Aircraft (VLA) Configuration

Sitio¹,

Kim²,

Lee³

2013

International Journal of Aeronautical and Space Sciences

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“…The vertex-based code on the other hand performs a larger amount of calculations when fluxes are computed, comparing the number of edges to each node with the number of cell neighbors of one cell (Mavriplis, 2007 …”

Section: Description Of the Cfd Codesmentioning

confidence: 99%

“…The second order dissipation coefficient, which is multiplied with a pressure switch (in order to activate it only in regions where necessary), is set to 0.5 and the fourth order to 0.02. It is important to introduce a small enough level of artificial dissipation, while retaining a converging solution, from an accuracy point of view (Mavriplis, 2007). The turbulent quantities are discretized with a second order up-wind scheme.…”

Section: Edgementioning

confidence: 99%

Comparing Different CFD Methods Accuracy in Computing Local Boundary Layer Properties

Pettersson

Rizzi

2009

Engineering Applications of Computational Fluid Mechanics

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ABSTRACT:In aeronautical applications wind tunnels are often not capable of producing high Reynolds numbers which are achieved at free flight conditions. Today CFD methods are often used as a tool to estimate scale effects. CFD methods are commonly used to predict flow features at Reynolds numbers higher than what the aircraft model is subject to in the wind tunnel, and at higher Reynolds number than the turbulence model has been calibrated to. The investigation of local boundary layer properties could give useful information when the wind tunnel data is scaled to free flight conditions-the question is whether the CFD methods compute these in a consistent manner when there is a large spread in Reynolds number. This work compares two different CFD solvers and two different turbulence models' accuracy in computing local boundary layer properties compared to wind tunnel measurements.

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“…Among the advantages of the method are a compact scheme stencil, easy parallel implementation of the scheme, and flexibility in choice of a computational mesh. The above advantages make a higher order DG scheme potentially attractive for industrial CFD applications and in recent years the method received a lot of attention in the literature [6,33,35,36]. In the past decade the intensive study of DG methods has been performed in Central Aerohydrodynamic Institute (TsAGI) in Russia in collaboration with the NUMECA International [49,50,52].…”

Section: Introductionmentioning

confidence: 99%

Application of a Higher Order Discontinuous Galerkin

Wolkov

Hirsch

Petrovskaya

2011

Math. Model. Nat. Phenom.

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Abstract. We discuss the issues of implementation of a higher order discontinuous Galerkin (DG) scheme for aerodynamics computations. In recent years a DG method has intensively been studied at Central Aerohydrodynamic Institute (TsAGI) where a computational code has been designed for numerical solution of the 3-D Euler and Navier-Stokes equations. Our discussion is mainly based on the results of the DG study conducted in TsAGI in collaboration with the NUMECA International. The capacity of a DG scheme to tackle challenging computational problems is demonstrated and its potential advantages over FV schemes widely used in modern computational aerodynamics are highlighted.

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Unstructured-Mesh Discretizations and Solvers for Computational Aerodynamics

Cited by 79 publications

References 75 publications

Grid Discretization Study for the Efficient Aerodynamic Analysis of the Very Light Aircraft (VLA) Configuration

Grid Discretization Study for the Efficient Aerodynamic Analysis of the Very Light Aircraft (VLA) Configuration

Comparing Different CFD Methods Accuracy in Computing Local Boundary Layer Properties

Application of a Higher Order Discontinuous Galerkin

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