Dynamic response of vortex breakdown flows to a pitching double-delta wing

Liu, Jian; Luo, Kun; Sun, Haixin; Huang, Yong; Liu, Zhitao; Xiao, Zhixiang

doi:10.1016/j.ast.2017.10.008

Cited by 22 publications

(3 citation statements)

References 27 publications

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“…Similar flow phenomena were also reported by Myose et al 13 and Ericsson and Lars. 14 Recently, Liu et al 15,16 carried out numerical studies on the unsteady characteristics of vortical flow features over double-delta wings during pitching (k = 0-1.0), with the results suggesting a phase shift of the vortex breakdown location due to the pitching oscillation.…”

Section: Introductionmentioning

confidence: 99%

Investigation on lift characteristics of a double-delta wing pitching in various reduced frequencies

Zhao

Liu

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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The unsteady lift characteristics of a double-delta wing were studied using both experimental and numerical approaches, which were also compared with a single-delta wing with the same main wing sweep angle. It was found that by increasing the reduced frequency of pitching, the hysteresis effect of lift was magnified. Moreover, in the high reduced frequency case k = 0.48, the difference between the lift coefficients of single- and double-delta wings became rather subtle. The wing surface pressure distribution results indicated the flow phenomenon of dramatic lift losses was due to the effect of lower surface suction during the wing being pitched downstroke. It was observed that, as the reduced frequency became sufficiently high, the virtual camber effect induced by pitching could dominate the flow field, which would mitigate the impact of wing geometry on the lift characteristics.

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Section: Introductionmentioning

confidence: 99%

Investigation on lift characteristics of a double-delta wing pitching in various reduced frequencies

Zhao

Liu

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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show abstract

“…Then, it had a good application in studying the dynamic stall of delta wings. Liu et al [13,14] implemented a finite, volume-based solver, with a rigid moving mesh and delayed detached eddy simulation (DDES), to analyze the effect of the reduced frequency (RF) on the burst point (BP), helical mode instability, pressure fluctuations, and dynamic pitching stability of a delta and double-delta wings (DW and DDW) in detail. They observed that all the pitching motions postponed the vortex breakdown, and the timeaveraged location of the BP has different changes in three sections, divided by a pair of critical RFs, which has been found in several previous experiments.…”

Section: Introductionmentioning

confidence: 99%

Comparative Study of Dynamic Stall between an Aircraft Airfoil and a Wind Turbine Airfoil in an Air–Particle Flow

Jin

Guo

et al. 2021

Applied Sciences

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Dynamic stall in clean air flow has been well studied, but its exploration in air–particle (air–raindrop or air–sand) flow is still lacking. The aerodynamic performance loss of aircraft (NACA0012) and wind turbine (S809) airfoils and their differences during the hysteresis loop at different pitching parameters are also poorly understood. As shown in this paper, the reduced frequency has little effect on the value of the maximum lift coefficient increment caused by particles, but a larger one can enhance the hysteresis effect and drag the angle of attack, at which the maximum increment is obtained, from the up stroke to the down stroke. The large lift coefficient increments of two airfoils and their difference also have a similar change trend with the reduced frequency. Compared to that of NACA0012 airfoil, the increments of S809 airfoil are obviously greater at three mean angles of attack, especially at 8°, which is the commonly used operating angle. In addition, the angle of attack, at which the maximum lift coefficient is obtained, can be significantly changed by particles in two regions: one is under the effect of deep stall, the other is under the effect of light stall at a low, reduced frequency.

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“…Owing to the possibility of unstable or structural failure, nonlinear anomalies of an airfoil/wing have created great interest. Three of the most common causes of nonlinearity are high angle of attack, transonic flow, and elastic structure [9][10][11][12]. Two-dimensional wind tunnel experiments were conducted to investigate the buffeting flow over a static airfoil and an oscillating pitching airfoil [13][14].…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Wind-Tunnel Wall Effects on Lift and Drag Characteristics of NACA 0012 Airfoil

Abobaker

Elfaghi

Addeep

2020

CFDL

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Possible interference effects of the wind tunnel walls play an important role especially for measurements in closed-wall test sections. In this study, a numerical analysis of two-dimensional subsonic flow over a NACA 0012 airfoil at different computational domain heights, angles of attack from 0o to 10o, and operating Reynolds number of 6×106 is presented. The work highlights the role of computational fluid dynamics (CFD) in the investigation of wind tunnel wall effect on lift curve slope correction factor (Ka). The flow solution is obtained using Ansys Fluent software by solving the steady-state continuity and momentum governing equations combined with turbulence model k-v shear stress transport (SST-K?). The numerical results are validated by comparing with the available experimental measurements. Calculations show that the lift curve slope correction results are very close to the published data.

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Dynamic response of vortex breakdown flows to a pitching double-delta wing

Cited by 22 publications

References 27 publications

Investigation on lift characteristics of a double-delta wing pitching in various reduced frequencies

Investigation on lift characteristics of a double-delta wing pitching in various reduced frequencies

Comparative Study of Dynamic Stall between an Aircraft Airfoil and a Wind Turbine Airfoil in an Air–Particle Flow

Numerical Study of Wind-Tunnel Wall Effects on Lift and Drag Characteristics of NACA 0012 Airfoil

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