On Vortical Flow Structures at Wing Stall and Beyond

Zarutskaya, T.; Arieli, Rimon

doi:10.2514/6.2005-4913

Cited by 17 publications

(20 citation statements)

References 8 publications

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“…There is a general agreement that SCs are dynamic structures that can be unstable, i.e., they can change in number and size or even move in the spanwise direction of a wing without any change in conditions, e.g. . In, it has been shown that a localized spanwise disturbance stabilize the flow in a single SC at the centre of a rectangular wing.…”

Section: Introductionmentioning

confidence: 77%

“…Although some extensive experimental studies have been published in the past on SCs, e.g., this is not the case for CFD simulations. To the authors' best knowledge, the only existing computational analysis is that of Zarutskaya and Arieli, who used RANS simulations and examined SCs on a NACA 0012 and a supercritical NASA SC2 airfoil at Reynolds (Re) number of 0.39 10 6 and 4.6 10 6 .…”

Section: Introductionmentioning

confidence: 99%

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Experimental and computational analysis of stall cells on rectangular wings

2013

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The present paper is the second part of a combined (experimental and computational) study on stall cells (SCs) on a rectangular wing. In the first part, tuft data were used in order to geometrically characterize a stabilized SC resulting from a localized spanwise disturbance introduced by a zigzag tape. Here, pressure measurements on the model and in the wake and aerodynamic polars at midspan are reported. The wing model had an aspect ratio value of 2, the Reynolds number was 10 6 and the range of angles of attack (a) was from À6 to 16. Experimental results confirm previous findings. Furthermore, two-dimensional and three-dimensional Reynolds Averaged Navier-Stokes RANS simulations are used in order to better understand the structure of SCs. 3D simulations reproduce the experimental data with a 3 delay in a and permit a qualitative analysis. It is found that the SC vortices start normal to the wing surface and extend downstream in the wake; the evolution of the SC vortices in the wake is in strong interaction with the separation line vortex and the trailing edge line vortex; as the SC vortex develops downstream in the wake, its centreline is contracted towards the SC centre; the wing wake is pushed upstream at the centre of the SC and downstream at the sides by the SC vortices; spanwise lift and drag distributions always attain their minimum at the SC centre.

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Section: Introductionmentioning

confidence: 77%

Section: Introductionmentioning

confidence: 99%

Experimental and computational analysis of stall cells on rectangular wings

2013

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“…This closely follows the CFD study presented in [1]. The physical content was inspired by these CFD findings, as well as by aerodynamics theory and the wind-tunnel results of Winkelmann and Barlow [6], Weihs and Katz [7], Broeren and Bragg [8], Zarutskaya and Arieli [9], Schewe [4], and others. The consensus is over lift cells that are fairly regular, with "mushroom" footprints in the wall friction lines and a natural spacing of two chords or a little more.…”

Section: Introductionmentioning

confidence: 83%

Prediction of Lift Cells for Stalling Wings by Lifting-Line Theory

Spalart

2014

AIAA Journal

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“…The behavior of stall-cells at lower Reynolds numbers is more controversial: recent studies from Broeren and Bragg (2001) found no span-wise time-fluctuations at Re = 0.30 × 10 6 , contrarily to the work of Zarutskaya and Arieli (2005), reporting rather irregular motions at Re = 0.39 × 10 6 . Recent works from Rodriguez and Theofilis (2010) using bi-global linear-instability analysis showed topological similarities between laminar separation bubbles and stall-cells, in terms of modal instability-components.…”

Section: Frequency Content and Dynamicsmentioning

confidence: 99%

“…In these high aspect-ratio rotating-wings, the radial flow is the driver of the instability which brings to the development of cellular structures preventing the centrifugal increase of the radial-velocity distribution up to the tip. In computational fluid dynamics, a substantial amount of research has been devoted to determine the effect on the pressure distribution and loading in low aspect-ratio wings (e.g., Zarutskaya and Arieli 2005;Taira and Colonius 2001). In particular, Taira and Colonius (2001) concluded that in low aspectratio wings, the stall-cells regime is an intermediate state which persists till the wake degenerates in a pure 2D Karman-shedding.…”

Section: Loading Distributionmentioning

confidence: 99%