Mesh adaptation strategies for problems in fluid dynamics

Baker, Timothy J.

doi:10.1016/s0168-874x(96)00032-7

Cited by 164 publications

(90 citation statements)

References 54 publications

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“…Mavriplis, 15 Owen, 16 and Baker 17 provide surveys of grid generation and adaptation techniques. Hybrid methods 18 treat the highly anisotropic regions of the domain as separate semi-structured zones lacking the generality to treat changes in the topology of these anisotropic regions off body.…”

Section: -14mentioning

confidence: 99%

“…19,[21][22][23][24] The metric-based adaptation process has two principle components: determining an improved resolution request and creating an improved grid that satisfies that request. The improved resolution request is commonly based on local error estimates 17,19,25,26 and can include the effect of local errors on a global output quantity. 11,27,28 The use of anisotropic grid metrics has become a very standard way to specify a resolution request, but it does have limitations.…”

Section: -14mentioning

confidence: 99%

“…This has also been a popular technique for structured grid methods, 17 because of the fixed connectivity. A node location is adjusted with the neighboring node locations fixed to produce a Gauss-Seidel style relaxation scheme.…”

Section: Iiia Node Movementmentioning

confidence: 99%

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Parallel Anisotropic Tetrahedral Adaptation

Park¹,

Darmofal

2008

46th AIAA Aerospace Sciences Meeting and Exhibit

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An adaptive method that robustly produces high aspect ratio tetrahedra to a general 3D metric specification without introducing hybrid semi-structured regions is presented. The elemental operators and higher-level logic is described with their respective domaindecomposed parallelizations. An anisotropic tetrahedral grid adaptation scheme is demonstrated for 1000-1 stretching for a simple cube geometry. This form of adaptation is applicable to more complex domain boundaries via a cut-cell approach as demonstrated by a parallel 3D supersonic simulation of a complex fighter aircraft. To avoid the assumptions and approximations required to form a metric to specify adaptation, an approach is introduced that directly evaluates interpolation error. The grid is adapted to reduce and equidistribute this interpolation error calculation without the use of an intervening anisotropic metric. Direct interpolation error adaptation is illustrated for 1D and 3D domains.

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Section: -14mentioning

confidence: 99%

Section: -14mentioning

confidence: 99%

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Parallel Anisotropic Tetrahedral Adaptation

Park¹,

Darmofal

2008

46th AIAA Aerospace Sciences Meeting and Exhibit

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“…There are many methods available for the generation of tetrahedral meshes [14][15][16] and they are typically based on either advancing front or Delaunay triangulation ideas. In our work, an automatic advancing-front method is used for mesh generation.…”

Section: Unstructured Tetrahedral Mesh Generationmentioning

confidence: 99%

Numerical and Mesh Resolution Requirements for Accurate Sonic Boom Prediction of Complete Aircraft Configurations

Choi

Alonso

Weide

2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

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In this paper we conduct a careful study to assess the numerical mesh resolution requirements for the accurate computation of sonic boom ground signatures produced by complete aircraft configurations. The details of the ground signature can be highly dependent on the accurate prediction of the pressure distribution in the near-field of the aircraft. For this purpose it is necessary to describe the geometric detail of the configuration including the wing, fuselage, nacelles, diverters, etc. and to accurately capture the propagation of shock and expansion waves at large distances from the fuselage centerline. Unstructured, adaptive mesh technologies are ideally suited for this purpose since they use mesh points only in the appropriate locations within the flow field. In this work, we consider a supersonic business jet configuration (SBJ) which was tested at the NASA Langley Research Center and for which experimental near-field data was extracted at several locations underneath the flight track. The propagation of these near-field signatures from different altitudes can be shown to result in near N-wave ground booms. In order to examine the effect of both nacelles and empennage, results for three test cases are presented. These test cases represent the complete configuration with the large nacelles, the configuration without the nacelles, and the configuration without the nacelles and empennage. Inviscid solution adaptive unstructured meshes with up to 7.2 million nodes and 42.1 million tetrahedra are used to calculate the pressure distributions at several locations below each configuration where comparisons with experimental data are performed. All near-field pressure distributions are propagated to the ground (from and altitude of 50,000 ft) to predict the ground boom and the perceived noise level of the ground signature. For each case, the minimum number of mesh nodes and elements and the levels of refinement needed for accurate computations of near-field pressure distribution and ground boom signature are discussed. INTRODUCTION SONIC boom phenomena is one of the main reasons preventing the acceptance of supersonic flight over populated areas. The importance of minimizing the environmental impact cannot be understated. In addition, the business case for low-boom supersonic aircraft is also quite compelling: a much larger market can be found should the aircraft be allowed to fly supersonically over land. For these reasons research efforts have been recently focused on various techniques for sonic boom mitigation.1-7 However, before sonic boom minimization design work can be credibly carried out, the accurate prediction of the fundamental sonic boom propagation problem has to be addressed in detail.By the time the pressure disturbance created by an airplane reaches the ground, most boom signatures develop into the well-known N-wave shape. This sig- * Graduate Student, AIAA Member nature is such that it contains two strong shocks at its beginning and end, causing a high perceived loudness (pldB). The propagation o...

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“…There have been several extensive reviews of mesh adaption approaches for CFD (e.g., see Baker 1 and McRae 2 ); however much of this work has focused on methods for actually performing the adaption rather than the approach for driving the mesh adaptation. This paper examines several different criteria for driving a mesh adaptation scheme.…”

Section: Introductionmentioning

confidence: 99%

Strategies for Driving Mesh Adaptation in CFD (Invited)

Roy

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This paper examines different approaches for driving mesh adaptation and provides theoretical developments for understanding the relationship between discretization error, the numerical scheme, and the mesh. Discrete and continuous equations governing the transport of discretization error are developed and it is shown that the truncation error acts as the local source for these equations. Examination of the truncation error in generalized coordinates provides insight into the role of mesh quality (mesh stretching for the 1D case) in the discretization error. Numerical results are presented for 1D steady-state Burgers equation at Reynolds numbers of 32 and 128. Four different approaches for driving mesh adaption are implemented for this case: solution gradients, solution curvature, discretization error, and truncation error. The truncation-error based adaption is shown to provide superior results for both cases. Finally, two approaches for estimating the truncation error are also discussed which would allow truncation error-based adaption to be implemented for complex numerical methods.

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Mesh adaptation strategies for problems in fluid dynamics

Cited by 164 publications

References 54 publications

Parallel Anisotropic Tetrahedral Adaptation

Parallel Anisotropic Tetrahedral Adaptation

Numerical and Mesh Resolution Requirements for Accurate Sonic Boom Prediction of Complete Aircraft Configurations

Strategies for Driving Mesh Adaptation in CFD (Invited)

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