Vortical substructures in the shear layers forming leading-edge vortices

Mitchell, Anthony; Molton, Pascal; Barberis, D.; Délery, Jean

doi:10.2514/6.2001-2424

Cited by 21 publications

(11 citation statements)

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“…Fig. 15 displays the resolved turbulent kinetic energy along the vortex core compared with experimental data [51]. As the grid is resolved the experimental peak is reached, although the computation required 10.5 million unstructured cells to attain the experimental level of resolved turbulent kinetic energy.…”

Section: Numerical Dissipationmentioning

confidence: 99%

Computational challenges in high angle of attack flow prediction

Cummings

Forsythe

Morton

et al. 2003

Progress in Aerospace Sciences

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Aircraft aerodynamics have been predicted using computational fluid dynamics for a number of years. While viscous flow computations for cruise conditions have become commonplace, the non-linear effects that take place at high angles of attack are much more difficult to predict. A variety of difficulties arise when performing these computations, including challenges in properly modeling turbulence and transition for vortical and massively separated flows, the need to use appropriate numerical algorithms if flow asymmetry is possible, and the difficulties in creating grids that allow for accurate simulation of the flowfield. These issues are addressed and recommendations are made for further improvements in high angle of attack flow prediction. Current predictive capabilities for high angle of attack flows are reviewed, and solutions based on hybrid turbulence models are presented. Contents

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Section: Numerical Dissipationmentioning

confidence: 99%

Computational challenges in high angle of attack flow prediction

Cummings

Forsythe

Morton

et al. 2003

Progress in Aerospace Sciences

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“…Details of the experiment, as well as additional data, are presented by Mitchell et.al. 41 . The results shown in Fig.…”

Section: Onera 70 O Sweep Delta Wingmentioning

confidence: 99%

DES Grid Resolution Issues for Vortical Flows on a Delta Wing and an F-18C

Morton

Steenman

Cummings

et al. 2003

41st Aerospace Sciences Meeting and Exhibit

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An assessment of unstructured grids for use in Detached-Eddy Simulations (DES) of vortical flowfields over two configurations, a 70 degree delta wing and an F-18C are presented. The role of the grid in detached eddy simulations of vortical flowfields, including complex features such as vortex breakdown, is assessed on a delta wing with comparison to wind tunnel data. Adaptive mesh refinement is applied to the delta wing grid to improve the focus region aft of the vortex breakdown where massively separated flow exists and unsteady pressures are generated that could impact the loads on vertical tails of more complex configurations. The adaptively refined mesh is compared to the baseline mesh to determine the advantage of the adaptive mesh refinement approach for vortex breakdown. The focus region grid resolution is then applied to an F-18C in the region of the vortex generat ed from the leading edge extension (LEX). The resulting unsteady tail loads are compared to flight test data from the NASA F-18 HARV database. This paper represents one of the first times adaptive mesh refinement will be applied to a detached eddy simulati on of a flight vehicle configuration.

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“…Interaction of the primary vortex with the boundary layer on the wing upper surface, gives rise to secondary vortices. In addition, the three-dimensional "sheet" feeding the leading-edge vortex is known to support both steady and unsteady coherent substructures [58,60,61,62] associated with shear-layer instabilities, and with unsteady boundary-layer separation and vorticity ejection on the wing upper surface.…”

Section: Leading-edge Vortex Control On a Delta Wingmentioning

confidence: 99%