Visualization and wake surveys of vortical flow over a delta wing

Payne, F. M.; Ng, Tammy; Nelson, Robert C.; Schiff, Lewis B.

doi:10.2514/3.9864

Cited by 123 publications

(35 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For instance, Payne et al [3] conducted flow visualization studies, providing useful conclusions about vortex breakdown.Özgören et al [4] and Ol and Gharib [5] experimentally studied the vortex structure in a water tunnel combining flow visualization with PIV measurements. Honkan and Andreopoulos [6] conducted three-dimensional wind tunnel vorticity measurements combining them with flow visualization.…”

Section: Introductionmentioning

confidence: 98%

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

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

show abstract

Section: Introductionmentioning

confidence: 98%

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

“…17,18 Even if these unsteady phenomena persist with an increase in the freestream Mach number, the behavior of the whole vortical flow is modified in the transonic regime.…”

Section: Introductionmentioning

confidence: 98%

Compressibility effects on the vortical flow over a 65° sweep delta wing

2010

View full text Add to dashboard Cite

Dynamically stretching and retracting wingspan has been widely observed in the flight of birds and bats, and its effects on the aerodynamic performance particularly lift generation are intriguing. The rectangular flat-plate flapping wing with a sinusoidally stretching and retracting wingspan is proposed as a simple model for biologically inspired dynamic morphing wings. Numerical simulations of the low-Reynolds-number flows around the flapping morphing wing are conducted in a parametric space by using the immersed boundary method. It is found that the instantaneous and time-averaged lift coefficients of the wing can be significantly enhanced by dynamically changing wingspan in a flapping cycle. The lift enhancement is caused by both changing the lifting surface area and manipulating the flow structures responsible to the vortex lift generation. The physical mechanisms behind the lift enhancement are explored by examining the three-dimensional flow structures around the flapping wing. C 2014 AIP Publishing LLC. [http://dx.

show abstract

“…In the past few decades, vortex breakdown phenomena due to leading edge flow separation from highly swept delta wing had been studied extensively by Hall (1972), Wentz and Kohliman (1971), Jarrah (1988) and Payne et al (1991). Moreover, Herbst (1983), Polhamus (1971Polhamus ( , 1984 gave an important conclusion that the vortex-dominated flow structure over delta wing induces a vortex lift which is crucial to the performance of delta wing at high AOA, Shi et al (1987) and Visser et al (1988) demonstrated that the length of vortex core prior to breakdown can be effectively extended by proper arrangement of blowing.…”

Section: Introductionmentioning

confidence: 99%

Non-uniform recovery of vortex breakdown over delta wing in response to blowing along vortex core

Kuo

Lin

1996

Experiments in Fluids

View full text Add to dashboard Cite

The transient characteristics of vortical structure over delta wing are studied experimentally when subject to single along-core blowing perturbation. Two half delta wing models with different sweep angle A = 60 ° and A = 75 ° are investigated in this study. For A = 75 °, the transient location of the onset of vortex breakdown moves upstream monotonously toward the unperturbed location. However, for A = 60 °, there exists a chordwise region where the upstream propagation of the onset location of vortex breakdown is temporarily delayed. This delay causes the recovery process (upstream propagation) of the onset location of vortex breakdown to be "non-uniform". In fact, this non-uniform recovery may take on different appearance such as a plateau or overshoots and will last for several times of the convective time scale C/U~. Furthermore, the location of chordwise region corresponding to this delay depends strongly upon the angle of attack (AOA). In additions, the non-uniform recovering characteristic of the onset of vortex breakdown may not be observed at high AOA if the blowing rate is too low. The mechanism governing the nonuniform recovering characteristic is clearly verified through the LDA measurement and the phase-locked flow visualization. Evidently the mutual interaction between the primary vortex structure and the secondary vortex is the key mechanism that leads to non-uniform recovering character over delta wing with sweep angle of 60 ° 1

show abstract

Visualization and wake surveys of vortical flow over a delta wing

Cited by 123 publications

References 5 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

Compressibility effects on the vortical flow over a 65° sweep delta wing

Non-uniform recovery of vortex breakdown over delta wing in response to blowing along vortex core

Contact Info

Product

Resources

About