Effects of an Unsteady Morphing Wing with Seamless Side-Edge Transition on Aerodynamic Performance

Abdessemed, Chawki; Bouferrouk, Abdessalem; Yao, Yufeng

doi:10.3390/en15031093

Cited by 16 publications

(13 citation statements)

References 41 publications

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“…A hybrid RANS-LES technique was used to investigate the aerodynamic performance of an aerofoil with a downward, statically morphing trailing-edge flap (TEF). Morphing enhanced lift-todrag by 6% [44,45]. Similar results were reported for the aerodynamic and aeroacoustics responses of an aerofoil fitted with a harmonically morphing trailing edge flap [46].…”

Section: Introductionsupporting

confidence: 82%

Numerical investigation of the dynamic stall reduction on the UAS-S45 aerofoil using the optimised aerofoil method

Bashir,

Zonzini,

Longtin Martel

et al. 2023

Aeronaut. j.

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This paper investigates the effect of the optimised morphing leading edge (MLE) and the morphing trailing edge (MTE) on dynamic stall vortices (DSV) for a pitching aerofoil through numerical simulations. In the first stage of the methodology, the optimisation of the UAS-S45 aerofoil was performed using a morphing optimisation framework. The mathematical model used Bezier-Parsec parametrisation, and the particle swarm optimisation algorithm was coupled with a pattern search with the aim of designing an aerodynamically efficient UAS-45 aerofoil. The $\gamma - R{e_\theta }$ transition turbulence model was firstly applied to predict the laminar to turbulent flow transition. The morphing aerofoil increased the overall aerodynamic performances while delaying boundary layer separation. Secondly, the unsteady analysis of the UAS-S45 aerofoil and its morphing configurations was carried out and the unsteady flow field and aerodynamic forces were analysed at the Reynolds number of 2.4 × 106 and five different reduced frequencies of k = 0.05, 0.08, 1.2, 1.6 and 2.0. The lift ( ${C_L})$ , drag ( ${C_D})$ and moment ( ${C_M})\;$ coefficients variations with the angle-of-attack of the reference and morphing aerofoils were compared. It was found that a higher reduced frequencies of 1.2 to 2 stabilised the leading-edge vortex that provided its lift variation in the dynamic stall phase. The maximum lift $\left( {{C_{L,max}}} \right)$ and drag $\left( {{C_{D,max}}} \right)\;$ coefficients and the stall angles of attack are evaluated for all studied reduced frequencies. The numerical results have shown that the new radius of curvature of the MLE aerofoil can minimise the streamwise adverse pressure gradient and prevent significant flow separation and suppress the formation of the DSV. Furthermore, it was shown that the morphing aerofoil delayed the stall angle-of-attack by 14.26% with respect to the reference aerofoil, and that the ${C_{L,max}}\;$ of the aerofoil increased from 2.49 to 3.04. However, while the MTE aerofoil was found to increase the overall lift coefficient and the ${C_{L,max}}$ , it did not control the dynamic stall. Vorticity behaviour during DSV generation and detachment has shown that the MTE can change the vortices’ evolution and increase vorticity flux from the leading-edge shear layer, thus increasing DSV circulation. The conclusion that can be drawn from this study is that the fixed drooped morphing leading edge aerofoils have the potential to control the dynamic stall. These findings contribute to a better understanding of the flow analysis of morphing aerofoils in an unsteady flow.

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Section: Introductionsupporting

confidence: 82%

Numerical investigation of the dynamic stall reduction on the UAS-S45 aerofoil using the optimised aerofoil method

Bashir,

Zonzini,

Longtin Martel

et al. 2023

Aeronaut. j.

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“…The slower morphing allowed the flow to remain attached throughout the morphing period. This overshoot in drag but not in lift was also seen in Abdessemed et al (2019Abdessemed et al ( , 2022, in which a higher overshoot was observed for high morphing frequencies.…”

Section: Dynamic and Static Comparisonmentioning

confidence: 54%

Aerodynamic Performance of Morphing and Periodic Trailing-Edge Morphing Airfoils in Ground Effect

Clements

Djidjeli

2023

J. Aerosp. Eng.

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Applying fish bone active camber morphing to the wing-in-ground effect to improve the aerodynamic efficiency was investigated 6 using computational fluid dynamics (CFD) at a Reynolds number of 320,000. Steady-static morphing was first carried out with Reynolds-7 averaged Navier-Stokes (RANS) equations in two dimensions for morphing start locations off (60%, 80%, and 90% chord), ground clear-8 ances (h=c ¼ 0.1, 0.2, 0.4, 1), and angles of attack (AoAs) 0°, 2°, 3°, 4°, and 12°. A morphing displacement (w te ) of 0.5% increased the 9 efficiency by 2.8% (compared to non-morphing in the ground effect) for the 3°AoA and 90% start location, and by 62% in comparison to the baseline unmorphed airfoil in freestream. Reducing h=c ¼ 1 to 0.1 increased the lift between 10% and 17%; the larger gain was with the highest morphing deflection. A key finding was that morphing the airfoil reduced the distance between the trailing edge and ground, enhancing the ground effect. Also, morphing at an earlier start location in the chord direction resulted in a smaller area beneath the airfoil, reducing the total pressure, which reduced the overall lift compared to a later morphing start location. Dynamic morphing at 1 Hz using URANS K-Omega-SST showed a similar amount of lift as static morphing but a slightly higher amount of drag. Reducing the period caused an initial overshoot in drag before settling. The dynamic ground effect showed higher efficiency at low AoAs compared to dynamic morphing in freestream, which is beneficial for aircraft to fly with less pitch. Finally, periodic morphing for h=c ¼ 0.1 using sinusoidal motion with morphing starting at 25% along the chord and 4°AoA was investigated between 0.05% to 0.15% w te and 0.5 to 3.5 Strouhal number.Periodically morphing at 0.125% w te and Strouhal number of 0.9 using DES simulations increased the efficiency by 5.4%; however, it reduced the lift by 0.7%, the drag reduced by 5.8%, and it showed Kelvin-Helmholtz instability at 9.8 Strouhal number.

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“…In aerodynamics, several studies have been carried out in order to define the shape of the trailing edge flap which allows the same deflection as the traditional flap, but which eliminates the discontinuities in the pressure coefficient distribution. To define the camber line of the morphing trailing edge, Abdessemed et al (2017) used a third order polynomial that is given by the Eq. ( 3) and they compared the results of the morphed airfoil to those of a flapped airfoil.…”

Section: Effect Of the Trailing Edge Flap Shape On The Hydrodynamic P...mentioning

confidence: 99%

Effects on cavitation inception of leading and trailing edge flaps on a high-performance hydrofoil

Arab

Augier

Deniset

et al. 2022

Applied Ocean Research

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Effects of an Unsteady Morphing Wing with Seamless Side-Edge Transition on Aerodynamic Performance

Cited by 16 publications

References 41 publications

Numerical investigation of the dynamic stall reduction on the UAS-S45 aerofoil using the optimised aerofoil method

Numerical investigation of the dynamic stall reduction on the UAS-S45 aerofoil using the optimised aerofoil method

Aerodynamic Performance of Morphing and Periodic Trailing-Edge Morphing Airfoils in Ground Effect

Effects on cavitation inception of leading and trailing edge flaps on a high-performance hydrofoil

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