A numerical technique for two-dimensional grid generation with grid control at all of the boundaries

Hsu, Ken Yuh; Lee, S.L

doi:10.1016/0021-9991(90)90056-7

Cited by 20 publications

(26 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…1; every eighth grid-line is plotted. The number of grid points in the streamwise, wallnormal, and spanwise directions was 1030 × 640 × 128 points respectively, and their distribution is determined by the elliptic mesh generation algorithm of Hsu and Lee [17]. The refinement of the mesh was based on experience gained previously in performing various DNS of flow in LP turbine cascades.…”

Section: Computational Detailsmentioning

confidence: 99%

Direct Computations of Boundary Layers Distorted by Migrating Wakes in a Linear Compressor Cascade

Zaki

Wissink

Durbin

et al. 2009

Flow Turbulence Combust

View full text Add to dashboard Cite

A Direct Numerical Simulation (DNS) of flow in the V103 Low-Pressure (LP) compressor cascade with incoming wakes was performed. The computational geometry was chosen largely in accordance with the setup of the experiments performed by Hilgenfeld and Pfitzner (J Turbomach 126: [493][494][495][496][497][498][499][500] 2004) at the University of the Armed Forces in Munich. The computations were carried out on the NEC-SX8 in Stuttgart using 64 processors and 85 million grid points. The incoming wakes stemmed from a separate DNS of incompressible flow around a circular cylinder with a Reynolds number of Re d = 3300 (based on mean inflow velocity and cylinder diameter). The boundary layer along the suction surface of the blade was found to separate and roll up due to a Kelvin-Helmholtz instability triggered by the periodically passing wakes. Inside the rolls further transition to turbulence was found to occur. The boundary-layer flow along the pressure surface did not separate, instead it underwent by-pass transition.

show abstract

Section: Computational Detailsmentioning

confidence: 99%

Direct Computations of Boundary Layers Distorted by Migrating Wakes in a Linear Compressor Cascade

Zaki

Wissink

Durbin

et al. 2009

Flow Turbulence Combust

View full text Add to dashboard Cite

show abstract

“…Computations of the two-dimensional configurations presented below were performed using structured grids, most of the calculations of the three-dimensional flow were also performed on structured meshes Structured grids were generated using the control technique of Hsu and Lee (1991). Using this technique, it was possible to control mesh spacing to the first point nearest the boundary (within one wall unit near solid surfaces), exert control over grid spacing tangential to the boundary, and also to maintain orthogonality of the mesh at all boundaries.…”

Section: Flow Configuration and Simulation Designmentioning

confidence: 99%

“…The incompressible flow around the configurations is predicted using a fractional step method developed for application in curvilinear coordinates. A grid generation scheme was developed using the control technique of Hsu and Lee (1991) for creation of structured meshes and used for gridding both geometries. This method assures orthogonality of the grid at boundaries and control over the spacing to the first mesh point within the domain.…”

mentioning

confidence: 99%

A New Approach to Prediction of Aircraft Spin

Squires¹

2002

View full text Add to dashboard Cite

Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathenng and maintaining the data needed and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302 Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)12-12-2002 REPORT TYPE Final Technical Report TITLE AND SUBTITLEA New Approach for Prediction of Aircraft Spin AUTHOR(S)Squires, Kyle D. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)Mechanical Unsteady Reynolds-averaged Navier-Stokes and Detached-Eddy Simulation are used to predict the flow around a forebody cross-section modeled by a rounded-corner square. The inlet velocity is inclined at 10 degrees to the main flow, the configuration modeling the massively separated flow around the forebody of a jet fighter rotating at high angle of attack. Simulations are performed at sub-and super-critical Reynolds numbers, corresponding to either laminar or turbulent boundary layer separation from the forebody. DES predictions show that following flow detachment, a chaotic and three-dimensional wake rapidly develops. The temporal evolution of the streamwise and lateral (side) forces acting on the body exhibit strong modulation due to the spanwise variation of the flow. Grid refinement deepens the structure of the resolved range of turbulent scales, predictions using unstructured meshes are also demonstrated to be equally accurate as those on structured grids. For the super-critical flow, the pressure distribution is close to the measured values, both the streamwise and side forces are in adequate agreement with measurements, and the effect of numerical parameters are well-understood. For the sub-critical flow, DES side-force predictions do not follow the experimental measurements far enough to achieve reversal. Possible causes for the discrepancy are discussed. SUBJECT TERMS

show abstract

“…The choice of the control functions has a large influence of the solution on the system. Some forms of the control functions are proposed by Thompson et al [3], Thomas and Middlecoff [20] as well as Hsu and Lee [21].…”

Section: System Of Elliptic Partial Differential Equationsmentioning

confidence: 99%

A Semi-Unstructured Turbomachinery Meshing Library With Focus on Modeling of Specific Geometrical Features

Stelldinger¹,

Giersch²,

Figaschewsky³

et al. 2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

View full text Add to dashboard Cite

Abstract. Computational Fluid Dynamics is widely used for the analysis and the design of turbomachinery blade rows. A well established method is the application of semi-unstructured meshes, that uses a combination of structured meshes in the radial direction and unstructured meshes in the axial as well as the tangential direction. This takes advantage of the approximately two dimensional flow field through the blade rows, whereby a fine radial discretization, excepting the near wall region, is not necessary. Otherwise, it is possible to discretize particular regions, e.g. the leading and trailing edge regions, in the axial and tangential direction without generating unnecessary nodes in the far field. The meshing approach is based on the projection of a two dimensional unstructured mesh defined at a reference surface. Once, the two dimensional mesh is generated the projection is achieved by transfinite interpolation from the reference surface to further radial surfaces using a structured mesh. Due to the modeling of geometrical features, especially fillets, advanced methods for the generation of structured meshes and mesh smoothing algorithms are required.The paper presents two different approaches for the generation of an appropriate structured mesh. The first is based on the solution of elliptic partial differential equations. The second approach is based on the split of the domain into fourteen appropriately arranged blocks. Furthermore, two smoothing methods for two dimensional unstructured meshes, a constrained Laplace smoothing and an optimization based approach, are presented. Regarding a more realistic representation of the geometry, methods for the modeling of cavities, variable clearance sizes and fillets are presented. Finally, a comparison of the smoothing techniques applied to a rotor passage is presented and the influence of chosen geometrical features on the flow solution is evaluated.

show abstract

A numerical technique for two-dimensional grid generation with grid control at all of the boundaries

Cited by 20 publications

References 0 publications

Direct Computations of Boundary Layers Distorted by Migrating Wakes in a Linear Compressor Cascade

Direct Computations of Boundary Layers Distorted by Migrating Wakes in a Linear Compressor Cascade

A New Approach to Prediction of Aircraft Spin

A Semi-Unstructured Turbomachinery Meshing Library With Focus on Modeling of Specific Geometrical Features

Contact Info

Product

Resources

About