Implicit Finite-Difference Procedures for the Computation of Vortex Wakes

Steger, J. L.; Kutler, Paul

doi:10.2514/3.60663

Cited by 135 publications

(21 citation statements)

References 6 publications

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“…In this sense we can relate the sign of eigenvalues with the upwind representation of the flow variables at the cell faces. The upwinding of the inviscid fluxes gives more freedom in devising implicit algorithms (Steger and Kutler [24] and Thomas and Walters [25]), since it loads up the diagonals of the implicit factors. Upwind differencing (Hartwich et al [26]), also, alleviates the necessity to add and to tune the numerical dissipation for numerical stability and accuracy as the schemes with central differencing that belong to the family of Beam and Warming Schemes (Beam and Warming [27]).…”

Section: Numerical Simulationmentioning

confidence: 99%

Block mesh refinement for incompressible flows in curvilinear domains

Georgantopoulou

Tsangaris

2007

Applied Mathematical Modelling

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A method for the solution of the Navier-Stokes equation for the prediction of flows inside domains of arbitrary shaped bounds by the use of Cartesian grids with block-refinement in space is presented. In order to avoid the complexity of the body fitted numerical grid generation procedure, we use a saw tooth method for the curvilinear geometry approximation. By using block-nested refinement, we achieved the desired geometry Cartesian approximation in order to find an accurate solution of the N-S equations. The method is applied to incompressible laminar flows and is based on a cell-centred approximation. We present the numerical simulation of the flow field for two geometries, driven cavity and stenosed tubes. The utility of the algorithm is tested by comparing the convergence characteristics and accuracy to those of the standard single grid algorithm. The Cartesian block refinement algorithm can be used in any complex curvilinear geometry simulation, to accomplish a reduction in memory requirements and the computational time effort.

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Section: Numerical Simulationmentioning

confidence: 99%

Block mesh refinement for incompressible flows in curvilinear domains

Georgantopoulou

Tsangaris

2007

Applied Mathematical Modelling

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“…There were a number of early groundbreaking applications coming from the CFD Branch at NASA Ames. Steger and Kutler [15] used the Beam-Warming implicit finite-difference procedures for the computation of unsteady vortex wakes. Kutler et al [13] applied the Beam-Warming schemes to viscous supersonic flow over symmetrical and asymmetrical external axial corners.…”

Section: Applications Of Beam-warming Approximate Factorization Algormentioning

confidence: 99%

Early development of implicit methods for Computational Fluid Dynamics at NASA Ames

Pulliam

2009

Computers & Fluids

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“…Several previous studies of two-dimensional vortex interaction show the distortion of the vortex cores into an ellipse caused by the strain rate field of one vortex action upon the other, (Moore and Saffman [52], Rossow [59,60], Steger and Kutler [64], Christiansen and Zabusky [12], Melander et al [46,47]). Melander et al [46] depict the flow of co-rotating vortices as observed from a frame of reference rotating with the vortex cores.…”

Section: Introductionmentioning

confidence: 96%

Multisensor Hot Wire Vorticity Probe Measurements of the Formation Field of Two Corotating Vortices

Romeos

Lemonis

Papailiou

2009

Flow Turbulence Combust

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Experimental evidence is reported, regarding the formation of a pair of co-rotating tip vortices by a split wing configuration, consisting of two half wings at equal and opposite angles of attack. Simultaneous measurements of the threedimensional vector fields of velocity and vorticity were conducted on a cross plane at a downstream distance corresponding to 0.3 cord lengths (near wake), using an in-house constructed 12-sensor hot wire anemometry vorticity probe. The probe consists of three closely separated orthogonal 4-wire velocity sensor arrays, measuring simultaneously the three-dimensional velocity vector at three closely spaced locations on a cross plane of the flow filed. This configuration makes possible the estimation of spatial velocity derivatives by means of a forward difference scheme of first order accuracy. Velocity measurements obtained with an X-wire are also presented for comparison. In this near wake location, the flow field is dictated by the pressure distribution established by the flow around the wings, mobilizing large masses of air and leading to the roll up of fluid sheets. Fluid streams penetrating between the wings collide, creating on the cross plane flow a stagnation point and an "impermeable" line joining the two vortex centres. Along this line fluid is directed towards the two vortices, expanding their cores and increasing their separation distance. This feeding process generates a dipole of opposite sign streamwise mean vorticity within each vortex. The rotational flow within the vortices obligates an adverse streamwise pressure gradient leading to a significant streamwise velocity deficit characterizing the vortices. The turbulent flow field is the result of temporal changes in the intensity of the vortex formation and changes in the position of the cores (wandering).

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Implicit Finite-Difference Procedures for the Computation of Vortex Wakes

Cited by 135 publications

References 6 publications

Block mesh refinement for incompressible flows in curvilinear domains

Block mesh refinement for incompressible flows in curvilinear domains

Early development of implicit methods for Computational Fluid Dynamics at NASA Ames

Multisensor Hot Wire Vorticity Probe Measurements of the Formation Field of Two Corotating Vortices

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