Aerodynamic and aeroelastic amplification in adaptive belt-rib airfoils

Campanile, Lucio Flavio; Anders, S.

doi:10.1016/j.ast.2004.07.007

Cited by 63 publications

(38 citation statements)

References 8 publications

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“…Studies have shown that the deformation shape and curvature of the morphing structure significantly affects the aerodynamic performance of the airfoils [9][10][11][12][13][14][15][16]. Sanders et al [9] conducted investigations on airfoils fitted with conventional flaps and conformal morphing trailing edges.…”

Section: Introductionmentioning

confidence: 99%

“…Results showed that the changes to the lift coefficient are dependent on the size, curvature and deflection angle of the deformed trailing edge and strongly curved deformed trailing edge can produce lower maximum lift-to-drag ratio and also increased the root bending moment coefficient compared to a gently curved deformed trailing edge. Campanile et al [13] developed a belt-rib morphing airfoil concept and proposed a model to study the possible actuation requirement reduction by exploiting the aerodynamic and aeroelastic amplification effects on airfoils. Effects of different deformation modes of morphing airfoil and conventional airfoil using hinged flap were quantitatively evaluated and results show that higher slope at trailing edge of belt-rib airfoil leads to large change in lift.…”

Section: Introductionmentioning

confidence: 99%

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Experimental investigation of aerodynamic performance of airfoils fitted with morphing trailing edges

Jawahar²,

Azarpeyvand³

2016

54th AIAA Aerospace Sciences Meeting

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General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. Full terms of use are available: http://www.bristol.ac.uk/pure/about/ebr-terms The aerodynamic performance and wake development of a NACA 0012 airfoil fitted with morphing trailing edges were studied using experimental and computational techniques. The NACA 0012 airfoil was tested with morphing trailing edges having various camber profiles with the same trailing edge tip deflection. The aerodynamic force measurements for the airfoil were carried out for a wide range of chord-based Reynolds number and angles of attack with trailing edge deflection angle of β = 5• and 10• . The experiments were validated with steady-state RANS simulation using SpalartAllmaras turbulence model. Experimental results show that the camber profiles of the morphing trailing edges significantly affect the airfoil's aerodynamic performance and effectiveness in improving the lift coefficient further by tailoring the morphing profiles. Hot-wire measurements showed that the downstream wake development can also be influenced as a result of changing the morphing trailing edge camber profile. It was found that highly cambered trailing edge profiles provide higher lift coefficients and increased maximum lift coefficient compared to moderately cambered profiles while the lift-to-drag ratio slightly decreases. Velocity contour plots show that the separation near the trailing edge is further delayed at high angles of attack for airfoils with highly chambered morphing trailing edge. This study shows that the effective design space of the morphing trailing edges can be expanded taking into account the optimal aerodynamic performance requirements. The study also suggests that in order to achieve optimum aerodynamic performance, independent surface morphing of the suction and pressure surface camber will be required to delay the onset of flow separation.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Experimental investigation of aerodynamic performance of airfoils fitted with morphing trailing edges

Jawahar²,

Azarpeyvand³

2016

54th AIAA Aerospace Sciences Meeting

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“…Aircraft wing and wind turbine blades are usually optimized for certain operating conditions and, as such, adaptive geometry change capabilities that enable active load control and gust load alleviation could significantly enhance the overall system performance (Ai et al, 2015;Barbarino et al, 2011;Campanile et al, 2004;Lachenal et al, 2013). Morphing structures have received growing interest from the research community as well as aviation, wind energy and automobile industries (Lachenal et al, 2013;Chopra 2002;Weisshaar 2013;Barbarino et al, 2011), owing to their excellent performance, lightweight and reduced structural complexity.…”

Section: Introductionmentioning

confidence: 99%

Design and mechanical testing of a variable stiffness morphing trailing edge flap

Azarpeyvand²

2017

Journal of Intelligent Material Systems and Structures

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Morphing structures that are both light-weight and conformal to the aerofoil are currently being considered as promising candidates for the next generation of aircraft high-lift systems. Utilizing spatially variable stiffness materials in morphing structures leads to a possible reduction in the actuation energy requirement and also enables geometric control over the deformed shape of the morphing structure, resulting in enhanced aerodynamic and aeroacoustic performance. In this study, a design optimization methodology has been developed to identify the required material stiffness variations of a morphing structure for target optimal deformed shapes. In the optimization scheme, a layer-wise sandwich beam model is used to predict the structural behaviour of the flap with a specific material stiffness variation. Two-dimensional fluid/structure static aeroelastic interaction analysis is performed in the design optimization. Finite element analysis and mechanical tests were also carried out for a chosen optimization result to study the actuation requirements and the capability of control over the deformed shape of the morphing trailing edge. Numerical and experimental results confirm the feasibility of the proposed optimization methodology for identifying the required stiffness variation in the core and also ways of using rapid prototyped honeycomb core to realize the honeycomb core stiffness variations are discussed.

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“…For low-speed flow, this structural model is complemented by unsteady airfoil theories (and an appropriate wake model) that provide the aerodynamic loading. However, there are situations in which the assumption of rigid cross sections cannot be justified, which can happen intentionally by design, as in the examples above [1][2][3][4][5] , or simply due to the 1 Lecturer, Department of Aeronautics, 355 Roderic Hill Building (rpalacio@imperial.ac.uk). Member AIAA 2 Associate Professor, Department of Aerospace Engineering, 3024 FXB Building (cesnik@umich.edu).…”

Section: Introductionmentioning

confidence: 99%

Low-Speed Aeroelastic Modeling of Very Flexible Slender Wings with Deformable Airfoils

Palacios¹,

S.²

2008

49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference &Amp;lt;br> 16th AIAA/ASME/AHS Ada

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A low-order aeroelastic model is introduced for very flexible high-aspect-ratio wings with adaptive airfoils. A geometrically-nonlinear beam-like model capable of capturing plate-like deformations has been coupled with a 2-D finite-state aerodynamic model with arbitrary airfoil deformations. The proposed approach results in a natural extension to the conventional way of analyzing high-aspect-ratio wings, with very little additional complexity. The control effectiveness of camber deformation is numerically investigated in some simple situations, including thin isotropic and anisotropic plates and a straight wing with a constant NACA4406 airfoil.

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Aerodynamic and aeroelastic amplification in adaptive belt-rib airfoils

Cited by 63 publications

References 8 publications

Experimental investigation of aerodynamic performance of airfoils fitted with morphing trailing edges

Experimental investigation of aerodynamic performance of airfoils fitted with morphing trailing edges

Design and mechanical testing of a variable stiffness morphing trailing edge flap

Low-Speed Aeroelastic Modeling of Very Flexible Slender Wings with Deformable Airfoils

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