Grid Generation for Fluid Mechanics Computations

Eiseman, Peter R.

doi:10.1146/annurev.fl.17.010185.002415

Cited by 118 publications

(32 citation statements)

References 32 publications

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“…The computational grid in the x-y plane is generated by using an algebraic multi-surface method [14] which gives desirable orthogonality at the body surface and at the inflow/outflow boundaries. The grid is clustered towards the wall and the leading edge but is uniform in z since the flow is assumed homogeneous in the spanwise direction.…”

Section: Resultsmentioning

confidence: 99%

Numerical study of leading-edge heat transfer under free-stream turbulence

Lele

Zhang

2001

39th Aerospace Sciences Meeting and Exhibit

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Section: Resultsmentioning

confidence: 99%

Numerical study of leading-edge heat transfer under free-stream turbulence

Lele

Zhang

2001

39th Aerospace Sciences Meeting and Exhibit

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“…Thompson et al (1985) provide an excellent reference to the fundamental concepts as well as the more advanced techniques in grid generation. Another excellent reference on numerical gridgeneration techniques is that of Eiseman (1985).…”

Section: Grid Generation Single Impeller Constructionmentioning

confidence: 99%

Steady and unsteady computation of impeller‐stirred reactors

Harvey

Rogers

1996

AIChE Journal

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“…1) The grid was generated using a three-dimensional transfinite interpolation technique, 28) i.e., 1) Generation of the one-dimensional line grids at all junctions of the domain surfaces with high density at all walls and in the region of the cylinder-flare junction, where high gradients exist, to ensure the accuracy of the simulations. 2) Generation of the two-dimensional surface grids for all of the domain boundary surfaces using the one-dimensional line grids as the interpolation boundaries and applying any geometric constraints.…”

Section: Cfd Code Grid Generation and Validationmentioning

confidence: 99%

Flare-Control Effectiveness at Hypersonic Speeds

Kontis

2004

Trans. Japan Soc. Aero. S Sci.

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The effects of flare control on the aerodynamic characteristics, performance, and stability of a cylindrical body under laminar and turbulent boundary layer conditions have been studied experimentally and computationally. The experimental study has been carried out in a hypersonic gun tunnel at a Mach number of 8.2 and a Reynolds number of 158,100, based on the cylinder diameter, at flare angles 0, 5, 10, 15, 20, 25 and 30 degrees and at pitch angles of À12 to 12 deg for the 10 deg flare case only. The surface flow was studied using the oil-dot technique. Some information regarding the shock layer was obtained from schlieren pictures. The effects of turbulence on onset of separation were also deduced from pressure measurements over the cylinder and the flare. The forces were measured with a three-component balance equipped with semiconductor strain gauges. The effects of centre of gravity (CG) location on the aerodynamic characteristics and in particular on the C M were examined. The results under turbulent conditions and zero-incidence were compared with numerical simulations performed using a 3-D time-marching Navier-Stokes code. The magnitude of the separated region, the minimum flare angle required to induce separation, and the effects of small-scale separation are detailed.

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Grid Generation for Fluid Mechanics Computations

Cited by 118 publications

References 32 publications

Numerical study of leading-edge heat transfer under free-stream turbulence

Numerical study of leading-edge heat transfer under free-stream turbulence

Steady and unsteady computation of impeller‐stirred reactors

Flare-Control Effectiveness at Hypersonic Speeds

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