Extended flexible trailing-edge on the flow structures of an airfoil at high angle of attack

He, Xinhua; Guo, Qinfeng; Wang, Jinjun

doi:10.1007/s00348-019-2767-5

Cited by 13 publications

(5 citation statements)

References 44 publications

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“…In contrast, this project investigates a combination of two methods using an active folding of the wing and a passive adaptation of the wing surface, as in natural flyers, to enhance the flight envelope of small aircraft. The investigated morphing wing is part of a common research project with the Beihang University (He et al, 2019;Guo et al, 2021). Both project partners investigate morphing W/T models in their facilities.…”

Section: Figurementioning

confidence: 99%

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Efficacy of an elasto-flexible morphing wing at high lift using fluid-structure-interaction simulations

Pflüger

Langsdorff

Breitsamter

2022

Front. Aerosp. Eng.

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The wide field of applications is the driving force behind the scientific interest in unmanned and micro air vehicles. For these aircraft, morphing wing technologies offer the possibility to adapt the aerodynamics to different flight stages. A morphing wing configuration with two elasto-flexible membrane wings is investigated numerically at a low Reynolds number of Re = 264000. The concept enables wing folding over a wide range and it allows the wing to adapt to changing aerodynamic loads. The focus is set on the benefits of the membrane in the high lift regime. Therefore, fluid-structure-interaction simulations are performed for the model equipped with a flexible and with a rigid wing. The comparison of the numerical results to data from previous experimental measurements show a good agreement. Compared with the rigid wing, the elasto-flexible membrane increases the gradient in the linear region and the maximum lift coefficient. In addition, the maximum lift coefficient is shifted to higher angles of attack. For selected wing positions and angles of attack, the aerodynamic behavior of the flexible and the rigid wing are investigated by means of the lift coefficient, the deformation of the membrane, the wall shear stresses and the wing surface pressure distribution. The deformation of the wing surface directly influences the area of flow separation at the extended wing and the separating leading-edge vortex at the folded wing. Both effects increase the generated lift of the wing with a flexible membrane.

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Section: Figurementioning

confidence: 99%

“…The passively deflecting camber of the wing was measured by static and dynamic deformations measurements. He et al deal with the changing camber of a two-dimensional membrane wing (He et al, 2019), at which they examine the fluid-structure-interaction.…”

Section: Introductionmentioning

confidence: 99%

Efficacy of an elasto-flexible morphing wing at high lift using fluid-structure-interaction simulations

Pflüger

Langsdorff

Breitsamter

2022

Front. Aerosp. Eng.

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“…Exploring the deformation detection method of steel strip with large deflection is a hot topic in structural safety research. Traditional metal structure deformation measurement mostly uses resistance strain gauge, digital camera, laser displacement sensor, 3D scanner, and remote automatic total station [5][6][7][8]. These technologies are mostly limited to small-scale fixed-point measurement, and the instruments used are large in volume and have complex installation, so that large-scale real-time detection is difficult to realize [9,10].…”

Section: Introductionmentioning

confidence: 99%

Large deflection deformation detection method of steel strip based on ultra-weak fiber bragg grating

et al. 2022

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Large deflection deformation of a steel strip is an important part of structural deformation detection. Deformation detection has been achieved using ultra-weak fiber Bragg gratings (FBGs), and the deformation reconstruction inversion algorithm of the tangent recursive algorithm has been analyzed theoretically. The strain distribution of the steel strips (2.5 m × 0.050 m × 0.002 m) with large deflection under different loads was obtained by pasting eight ultra-weak FBG sensors with spacing of 0.3 m on the surface of the strip. The steel strips deformation was inversed by tangent recursive algorithm, and deformation error under loading condition was analyzed by finite element simulation. The inversion value is compared with the theoretical value and the measured value, which proves the effectiveness and accuracy of the ultra weak FBG method proposed in this paper.Results show that the large deflection deformation of a steel strip under different loads can be reconstructed using the tangent recursive algorithm, and the relative errors of the coordinates of the sampling points are less than 6.21%. This paper provides a reference for the detection of structural deformation.

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“…He et al. 21 discussed the effect of the flexible trailing-edge plate on the flow structures and the corresponding fluid-structure coupling phenomenon at high AoA.…”

Section: Introductionmentioning

confidence: 99%

“…At present, literatures had focused on the effects of the parameters of the small flaps, such as the angle, 11,12 position 13,14 and plane shape, 15,18 and the effects of small flaps on different airfoil 16,17 or flexible flaps. 20,21 All the models used in the above studies were relatively small, especially with a small chord length size, resulting in a relatively low Reynolds number. The aerodynamic forces of a three segment airfoil were measured using a four-component balance in this study, and the effects of the bionic flap parameters (angle, length, shape and combination position) on the aerodynamic characteristics of the airfoil were explored systematically.…”

Section: Introductionmentioning

confidence: 99%

Experimental study on the effect of bionic flap parameters on airfoil aerodynamic performance

Hao

Gao

Shang

2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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The effects of bionic flap on airfoil performance were experimentally studied to provide theoretical support for the application of the bionic flap in aeronautical engineering. Seven kinds of bionic flaps were used to study the effects of the key flap parameters, including the flap angle, length, shape, and position, at a Reynolds number of Re = 0.8 × 106. At small angle of attacks (AoAs), the drag and pitching moment increased and the lift reduced when using the bionic flap. While at high AoAs, the lift increased and the drag reduced, which improved the airfoil stall characteristics. The configuration of deflection bionic flap had the smallest initial AoA for improving the airfoil stall characteristics in the seven kinds of bionic flaps. More than eight degrees of the effective AoA range for improving lift characteristics could be achieved. The maximum lift coefficient could be increased by 3.9%. Additionally, the control mechanisms of the flap under different flow conditions (attached flow and separated flow) were deeply studied. In the attached flow, the effective camber and thickness of the basic airfoil could be changed by the flap, resulting that the flow around the airfoil was affected, which in turn affected the Cl and the slope of the lift line. In the separated flow, the flap affected the flow around the airfoil by controlling the development of the trailing edge separation vortex. These research results confirmed the aerodynamic mechanisms for the formation of double layered feathers when birds land, and provided insight into application of bionic flaps in aeronautical engineering.

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Extended flexible trailing-edge on the flow structures of an airfoil at high angle of attack

Cited by 13 publications

References 44 publications

Efficacy of an elasto-flexible morphing wing at high lift using fluid-structure-interaction simulations

Efficacy of an elasto-flexible morphing wing at high lift using fluid-structure-interaction simulations

Large deflection deformation detection method of steel strip based on ultra-weak fiber bragg grating

Experimental study on the effect of bionic flap parameters on airfoil aerodynamic performance

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