A time-split finite-volume algorithm for three-dimensional flow-field simulation

Hung, C. M.; Kordulla, W.

doi:10.2514/6.1983-1957

Cited by 13 publications

(9 citation statements)

References 7 publications

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“…The horseshoe vortices wrap around the strut and ensure the diversion of the boundary layer around the appendage. The traihng structures decay slowly and interact with the flow downstream of the juncture [2]. The flow is completely 3D and becomes comphcated as the horseshoe vortex interacts with the boundary layer developed on the body surface.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of the Turbulent Flow around a Strut Mounted on a Plate

Ungureanu¹,

Lungu²

2009

AIP Conference Proceedings

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The research describes the flow features around a protuberance mounted on a plate. It aims at establishing an appropriate method to further design the geometry of a fm mounted on the ship hull with the flow around the stem may be controlled. For that purpose, a numerical simulation aimed at describing the flow field around a NACA0012 hydrofoil mounted on a plate is presented. Several geometric configurations are taken into account, e.g. flat or curved plate, straight or inclined hydrofoil. RANS equations are solved to compute the solution around the juncture. Closure to the turbulence is done by using the Spalart-AUmaras one-equation model and the results are compared. A FVM technique is employed to solve the problem numerically. H-C type grids are used for the PDE discretization.

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Section: Introductionmentioning

confidence: 99%

Numerical Simulation of the Turbulent Flow around a Strut Mounted on a Plate

Ungureanu¹,

Lungu²

2009

AIP Conference Proceedings

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“…To correct the erroneous occurrence of negative density in the flowfield and thereby allow a large CFL number to be used during the startup phase, the blunt body starting condition as suggested in Ref. 18 is used.…”

Section: Boundary and Initial Conditionsmentioning

confidence: 99%

Study of supersonic intersection flowfield at modified wing-body junctions

Lakshmanan

Tiwari

1993

AIAA Journal

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The problem of supersonic flow control using fillets and sweep for a wing-body junction has been investigated numerically using a three-dimensional Navier-Stokes code, which employs the MacCormack's time-split finite volume technique. An elliptic grid generation technique with direct control over spacing has been developed for constructing the grid at a filleted wing-body junction. The computed results for pressure distribution, particle paths, and limiting streamlines on the flat plate and fin surface for a swept fin show a decrease in the peak pressure on the fin leading edge and in the extent of the separated flow region. Moreover, the results for filleted juncture clearly show that the flow streamline patterns lose much of their vortical character with proper filleting. It has been demonstrated that fillets with a radius of three-and-one-half times the fin leading-edge diameter are required to weaken the vorticity in the horseshoe vortex by a factor of three for the Mach number and Reynolds number considered in the present study. Nomenclature a -speed of sound CFL = Courant-Friedrichs-Lewy number Cf = skin friction coefficient D = diameter of the fin E = total energy per unit mass £/ = specific internal energy, T/y(y -1) H = height of the fin / = index in % direction j = index in 17 direction k -index in f direction L£, L^ L{ = finite difference operators in £, 17, and f directions M = Mach number Pri -laminar Prandtl number Pr t -turbulent Prandtl number p = static pressure R = radius of the fillet at the juncture T = static temperature t = time q = vector of conserved variables u -velocity component in x direction v = velocity component in y direction w = velocity component in z direction x, y, z = global coordinates X Q = distance from the flat plate leading edge to fin leading edge y = ratio of specific heats, c p /c v At = time step used in the split operators d = boundary-layer thickness A = fin sweep angle X = second coefficient of viscosity, -%/* jLt = dynamic molecular viscosity £, y, f = body oriented coordinates p = density a = safety factor in the stability criteria equation w = vorticity magnitude Subscripts t2

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“…11. Governing EpIn the Eulerian formulation, the conservative equations in integral form for mass, momentum and energy with respect to a control volume V stationary in the inertial frame and enclosed by the control surface A are:…”

Section: Well-posed and Stable Boundary Conditionsmentioning

confidence: 99%

An assessment of numerical solutions of the compressible Navier-Stokes equations

Shang

1984

17th Fluid Dynamics, Plasma Dynamics, and Lasers Conference

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A time-split finite-volume algorithm for three-dimensional flow-field simulation

Cited by 13 publications

References 7 publications

Numerical Simulation of the Turbulent Flow around a Strut Mounted on a Plate

Numerical Simulation of the Turbulent Flow around a Strut Mounted on a Plate

Study of supersonic intersection flowfield at modified wing-body junctions

An assessment of numerical solutions of the compressible Navier-Stokes equations

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