Large Eddy simulation of a heaving wing on the Cusp of transition to turbulence

Badoe, C.; Xie, Zheng-Tong; Sandham, Neil D.

doi:10.1016/j.compfluid.2019.03.023

Cited by 11 publications

(3 citation statements)

References 38 publications

(40 reference statements)

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“…The results of the comparison are used to adjust the numerical model and parameters until satisfactory agreement is achieved. To this end, the adopted methodology in this study was validated with the experimental and numerical study of Badoe et al, 33 Chierenghin et al, 34 and Liu et al 35 The parameters used in the validation study included a Reynolds number of 2 3 10 4 and an angle of attack of 15°. The main discrepancy between the study's results was mainly due to different numbers of mesh elements and adopted boundary conditions.…”

Section: Validationmentioning

confidence: 99%

Investigation of aerodynamic and aeroacoustic behavior of bio-inspired airfoils with numerical and experimental methods

Güzey,

Aylı,

Kocak

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part C:

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This article presents numerical and experimental studies on the aerodynamic and aeroacoustic characteristics of the NACA0012 profile with owl-inspired leading-edge serrations for aeroacoustic control. The leading-edge serrations under investigation are in a sinusoidal profile with two main design parameters of wavelength and amplitude. The noise-suppressing ability of sinusoidal serrations is a function of several parameters such as amplitude, wavelength, inflow speed, angle of attack, which are examined in this study. Amplitude (A) and wavelength (λ) of the serration are varied between 1.25 and 2.5, 20 < λ < 60, respectively. The corresponding Reynolds numbers are between 1 and 3 × 105. The angle of attack for each configuration is changed between 4° and 16°. Forty different configurations are tested. According to the results, owl-inspired leading-edge serrations can be used as aeroacoustic control add-ons in blade designs for wind turbines, aircraft, and fluid machinery. Results show that the narrower and sharper serrations have a better noise reduction effect. Overall sound pressure level (SPL) reduces up to 20% for the configuration with the largest amplitude and smaller wavelength. The results also showed that serration amplitude had a distinct effect on aeroacoustic performance, whereas wavelength is a function of amplitude. At the smaller angle of attack values, AOA < 8°, the lift and drag coefficients are almost the same for both clean and wavy profiles. On the other hand, typically for angle of attack values more than 12° (after stall), when the angle of attack is increased, serration adversely affects aerodynamic performance.

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Section: Validationmentioning

confidence: 99%

Investigation of aerodynamic and aeroacoustic behavior of bio-inspired airfoils with numerical and experimental methods

Güzey,

Aylı,

Kocak

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…The SIMPLEC algorithm was employed for pressure-velocity coupling. Three levels of mesh density were evaluated, generated by a systematic 2 refinement of the reference structured block grid [41]. Aerodynamics coefficients at zero angle of attack were calculated and are presented in Table 7.…”

Section: Foldable Wing Design Schemesmentioning

confidence: 99%

Aerodynamic Analysis of a Logistics UAV with Foldable Bi-wing Configuration

Wang,

Lu,

Liu

et al. 2023

International Journal of Aerospace Engineering

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Herein, a twin-boom, inverted V-tailed unmanned aerial vehicle (UAV) featuring a foldable bi-wing configuration is proposed for logistics and transportation applications. We employed the Navier–Stokes solver to numerically simulate steady, incompressible flow conditions. By examining the effects of key design parameters on aerodynamic characteristics and bypass flow fields in a two-dimensional state, we were able to suggest a more optimized foldable wing design. Building on the two-dimensional analysis, we performed aerodynamic assessments of the three-dimensional aircraft geometry. Our results indicated that appropriate wing and gap parameters can significantly enhance lift characteristics, maintaining high lift even during large-angle flights. Specifically, when compared to a mono-wing, the lift coefficient of the bi-wing increased by 27.1% at a 14° angle of attack, demonstrating the effectiveness of our wing-and-gap design. Optimal aerodynamic performance was achieved when the gap distance equalled the chord length in both flow and vertical directions. Further, the right combination of airfoil configuration, wing axes angle, and wingspan can improve flow field aerodynamic characteristics, while also enhancing the wing’s stall capacity. The lift coefficient reached its maximum value at an angle of attack of 15°, which has the potential to reduce takeoff and landing distances, thereby enhancing the UAV’s overall safety.

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“…In recent years, the interaction of free-stream turbulence and a static or unsteady wing has attracted greater attention from researchers in the aeronautics (e.g. Chiereghin, Cleaver & Gursul 2017;Badoe, Xie & Sandham 2019;Zhang, Wang & Gursul 2023), acoustics (e.g. Lau, Haeri & Kim 2013;Bowen, Celik & Azarpeyvand 2023) and wind engineering (e.g.…”

Section: Introductionmentioning

confidence: 99%

Impact of large-scale free-stream turbulence on a pitching airfoil

Boye,

Djidjeli,

Xie

2024

Flow

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This paper investigates the impact of large-scale turbulence on the aerodynamic characteristics of a pitching wind turbine blade at Reynolds number 135 000, whose cross-section is a NACA0012 airfoil with constant chord length. Large-eddy simulations at reduced frequencies, $k_{red} = 0.05$ and 0.1, were validated against reference data from the literature. An efficient method capable of generating synthetic large-scale turbulence at the inlet was applied by using two streamwise integral length scales $L_{x} = 1c$ and 1.5 $c$ , which represent energetic turbulence eddies at the height where the wind turbine operates. For $k_{red}= 0.1$ , the change in the maximum lift coefficient at the dynamic stall angle near the maximum angle of attack is on average 20 % lower and during the downstroke it is on average 22 % lower, compared with the smooth inflow. A higher reduced frequency ( $k_{red} = 0.2$ ) apparently does not further change the lift, drag and moment coefficients, and the inflow turbulence disordered leading-edge vortices. The turbulent shear stress and the phase-averaged dispersive shear stress in the wake are of the same magnitude, but with negative and positive signs, respectively, suggesting that the large-scale phase-averaged fluctuations transfer momentum in the opposite direction compared with the turbulent fluctuations, reducing the drag on the suction-side flow, and subsequently increasing the averaged lift coefficient. This demonstrates the critical importance of the large-scale non-turbulent unsteadiness in the wake of a pitching wing.

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Large Eddy simulation of a heaving wing on the Cusp of transition to turbulence

Cited by 11 publications

References 38 publications

Investigation of aerodynamic and aeroacoustic behavior of bio-inspired airfoils with numerical and experimental methods

Investigation of aerodynamic and aeroacoustic behavior of bio-inspired airfoils with numerical and experimental methods

Aerodynamic Analysis of a Logistics UAV with Foldable Bi-wing Configuration

Impact of large-scale free-stream turbulence on a pitching airfoil

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