Separation ahead of Protuberances in Supersonic Turbulent Boundary Layers

Sedney, Raymond; Kitchens, Clarence W.

doi:10.2514/3.60658

Cited by 62 publications

(28 citation statements)

References 6 publications

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“…7h, these large oscillations are particularly restricted to the region close to the corner, where a secondary vortex is expected. While the flow organisation may vary significantly across different (Sedney 1973;Sedney and Kitchens 1977;Ozcan and Holt 1984), results suggest that the organisation is dominated by the main horseshoe vortex and the localised counter-rotating vortex at the corner for the present range of interactions (0.17 × 10 5 < Re δ u < 0.47 × 10 5 ). The proximity of the present conditions to the Re δ u ≈ 1 × 10 5 threshold-which is often regarded as an approximate limit for Reynolds number trend reversal in separation length correlations (Délery and Marvin 1986)-places the present interactions within a relatively complex regime whereby both viscous and inviscid forces play a significant role.…”

Section: Time-dependent Heat Transfermentioning

confidence: 96%

Reattachment heating upstream of short compression ramps in hypersonic flow

Estruch-Samper

2016

Exp Fluids

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Section: Time-dependent Heat Transfermentioning

confidence: 96%

Reattachment heating upstream of short compression ramps in hypersonic flow

Estruch-Samper

2016

Exp Fluids

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“…For better understanding each chord plane is advancing in the upward Y-direction of the domain. The flow separation from the fin surface can be compared to that of a flow separation from the blunt surface with height to width ratio of ~ 0.13 [4]. The current single planar fin case has a height to width ratio of ~ 0.11.…”

Section: Computed Shock Structures and Surface Pressuresmentioning

confidence: 99%

“…Hung and Buning [2], Hung and Kordullat [3] initially carried out simulations on a 3-D flat plate, in turbulent flow. Sedney and Kitchens [4] conducted experiments in supersonic regime involving spherical protuberances, the flow separation can be co-related to flow over blunt surfaces. In this study the detailed pressure and Mach number contours were presented.…”

Section: Introductionmentioning

confidence: 99%

Investigation of flow-field around a single generic planar fin using CFD

Sharma

Kumar

2019

SN Appl. Sci.

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The purpose of this paper is to initiate a 3-D non-spinning semi-circular missile model with a single generic planar fin and perform a computational analysis on it to understand the flow pattern around the fin. A freestream computational fluid dynamics analysis was done in the subsonic and supersonic Mach range, in which, the fluid behaviour was investigated using a two-equation turbulence model. A structured mesh was adopted to visualize the flow pattern around the fin. The aerodynamic coefficients were calculated for the model, and the predicted values were compared with the previous experimental results as well as the numerical results. This paper attempts to present all the possible flow visualizations which might help in better understanding of flow around missiles having planar fins. This work also attempts to establish a turbulent computational model for a single planar fin missile model for subsonic to supersonic range.

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“…Thus, the split operator contains the spatial flux derivatives in only one direction. The finite difference formulation in terms of the split operators can be expressed as (4) Each split operator consists of a predictor and a corrector step. During a specific numerical sweep, the inviscid fluxes are forward differenced in the prediction sequence and backward differenced in the correction step.…”

Section: Computational Proceduresmentioning

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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Separation ahead of Protuberances in Supersonic Turbulent Boundary Layers

Cited by 62 publications

References 6 publications

Reattachment heating upstream of short compression ramps in hypersonic flow

Reattachment heating upstream of short compression ramps in hypersonic flow

Investigation of flow-field around a single generic planar fin using CFD

Study of supersonic intersection flowfield at modified wing-body junctions

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