Measurements of circulation and vorticity in the leading-edge vortexof a delta wing

Visser, Kenneth D.; Nelson, Robert C.

doi:10.2514/3.11325

Cited by 76 publications

(31 citation statements)

References 16 publications

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“…All of the results were calculated from the hot-wire measurements. Visser and Nelson [7] justified the local semi-span to be a suitable length scale for delta wing planforms; therefore, the trailing edge semi-span was selected as a length scale. The results are presented for the five measurement planes, closer to the delta wing model from the left to the right.…”

Section: Resultsmentioning

confidence: 99%

“…Honkan and Andreopoulos [6] conducted three-dimensional wind tunnel vorticity measurements combining them with flow visualization. Visser and Nelson [7] measured the velocity field above a flat plate delta wing using hot-wire anemometry, thus acquiring vorticity and circulation distributions. Chu and Luckring [8] conducted experimental studies on a 65 • delta wing, investigating the effects of Reynolds and Mach numbers for different values of leading-edge bluntness.…”

Section: Introductionmentioning

confidence: 99%

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Turbulence Kinetic Energy Balance in the Wake of a Sharp-edged Highly Swept Delta Wing

Panagiotou

Sideridis

Yakinthos

et al. 2015

Flow Turbulence Combust

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Hot-wire measurements in the wake of a flat plate delta wing, at a fixed angle of attack, were carried-out in order to investigate its turbulence kinetic energy budget. The purpose of this study is to help acquire more information about the vortex structure formed in the wake region of the delta wing and to provide data for turbulence models' validation. Point measurements were conducted in five planes perpendicular to the flow, on a high spatial resolution two-dimensional measurement grid that allowed precise derivative calculations of the flow quantities needed for the derivation of the kinetic energy budget. The turbulence kinetic energy convection, production, viscous diffusion and turbulence diffusion terms were directly obtained from the experimental data, whereas dissipation and pressure diffusion terms were calculated indirectly using techniques presented and validated in previous studies. All of the terms of the turbulence kinetic energy budget, along with the velocity components and the Reynolds stresses, are presented and discussed.Keywords Delta wing · Hot-wire anemometry · Measurement · Turbulence kinetic energy balance · Vortex breakdown · Wake NomenclatureEnglish symbols C k convection term of the TKE budget D p pressure diffusion term of the TKE budget D t turbulence diffusion term of the TKE budget D v viscous diffusion term of the TKE budget e iso isotropic expression for the dissipation term of the TKE budget k turbulence kinetic energy per unit mass

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Turbulence Kinetic Energy Balance in the Wake of a Sharp-edged Highly Swept Delta Wing

Panagiotou

Sideridis

Yakinthos

et al. 2015

Flow Turbulence Combust

View full text Add to dashboard Cite

show abstract

“…Circulation has been postulated to grow approximatelylinearly with increasingdistance from the wing apex, upstream of the burst location. 9 Furthermore, the rate of circulation growth reportedly decreases aft of the midchord location; this has been attributed to the adverse pressure gradient imposed by the wing's trailing edge. 9 The present study was undertaken to quantify the circulation of the delta-wing primary vortices and to examine the variation of circulation with angle of attack and chordwise location for wing sweep angles of 60 and 70 deg.…”

Section: Introductionmentioning

confidence: 98%

“…For wing sweep angles less than 70 deg, maximum lift occurs approximately when the burst location reaches the apex, whereas for higher sweep angles, maximum lift is observed when the vortex bursts in the vicinity of the trailing edge. To shed light on the in uence of burst location on delta-wing lift and stall, both the variation of the primary vortex circulation 0.x/ along the chord and the vortex core distance above the wing z c are necessary because Presented as Paper 97-0743 at the AIAA 35th Aerospace Sciences Meeting, Reno, NV, Jan. [6][7][8][9]1997; received Feb. 24,1998; revision received Aug. 10,1998;accepted for publicationAug. 19,1998 the suction on the wing surface beneath the vortex core scales approximately with .0=z c / 2 .…”

Section: Introductionmentioning

confidence: 99%

Direct Measurement of Delta-Wing Vortex Circulation

Johari

Moreira

1998

AIAA Journal

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The circulation around a closed path encompassing the primary vortex of stationary delta wings has been investigated through the use of a novel ultrasound technique. Ultrasonic pulses propagating in clockwise and counterclockwise directions enclosed a xed path that was positioned perpendicular to the delta-wing root chord line. Circulation in the plane of the closed path then was determined from the transit-time difference between the clockwise and counterclockwise pulses. Half-delta wings with sweep angles of 60 and 70 deg were tested over a range of angles of attack up to 38 and 52 deg, respectively, and at chordwise distances of 35, 50, 65, and 80% from the wing apexes. Circulation increased monotonically with angle of attack for both sweep angles until it reached a maximum value, beyond which the total circulation decreased or remained nearly constant. The angle of attack associated with the maximum circulation is correlated with conditions resulting in feeding sheet interaction on the symmetry plane. At any angle of attack, circulation increased approximately linearly with increasing chordwise location as long as the feeding-sheet interaction was not present. Normalizing circulation by freestream velocity and local semispan collapsed the data at angles of attack prior to the interaction. The rate of circulation increase along the wing increased with angle of attack for both sweep angles. Vortex breakdown does not appear to have any direct in uence on the total circulation of delta-wing vortices.

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“…The size and strength of the leading-edge vortices increase with the angle of incidence, resulting in a substantial nonlinear lift increment. But the maximum lift of a delta wing is limited by a phenomenon known as vortex breakdown (Visser & Nelson 1993). …”

Section: Current Afosr Research Projectmentioning

confidence: 99%

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2001

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Measurements of circulation and vorticity in the leading-edge vortexof a delta wing

Cited by 76 publications

References 16 publications

Turbulence Kinetic Energy Balance in the Wake of a Sharp-edged Highly Swept Delta Wing

Turbulence Kinetic Energy Balance in the Wake of a Sharp-edged Highly Swept Delta Wing

Direct Measurement of Delta-Wing Vortex Circulation

Upgrade of the Computing and Visualization System for DNS/LES Research

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