Estimated performance of an adaptive trailing-edge device aimed at reducing fuel consumption on a medium-size aircraft

Diodati, Gianluca; Concilio, Antonio; Ricci, Sergio; Gaspari, Alessandro De; Huvelin, Fabien; Dumont, Antoine; Godard, Jean-Luc

doi:10.1117/12.2013685

Cited by 29 publications

(19 citation statements)

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“…Once the optimal morphing airfoil is obtained, the finite element models are automatically generated both for the single rib and for a complete wing section. Many numerical applications of this methodology have been reported in the framework of different European projects such as NOVEMOR [18] and SARISTU [19]. This paper reports the results of the first experimental validation of the proposed approach concerning a small scale wind tunnel model equipped with morphing leading and trailing edge.…”

Section: Design Manufacturing and Wind Tunnel Test Of A Morphing Winmentioning

confidence: 99%

Design, Manufacturing and Wind Tunnel Validation of a Morphing Compliant Wing

Gaspari

Riccobene

Ricci

2018

Journal of Aircraft

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The paper describes the activities performed at Politecnico di Milano in the framework of FP7-NOVEMOR Project aiming at the design, manufacturing and wind tunnel test of a wing model equipped with morphing leading and trailing edges based on compliant structures. Starting from the Reference Aircraft, i.e. a typical regional aircraft developed during NOVEMOR project, a small scale wind tunnel model has been derived to validate the proposed morphing concept and to correlate the numerical models in an experimental environment. A special attention has been devoted to the selection of the manufacturing technology due to the difficulty in realizing compliant structures with enough accuracy at a small scale level. After a short reminder of the tools developed for the design of variable camber morphing wings, the paper describes in details the design and manufacturing phases together with the functionality and wind tunnel tests.The results were used to validate the procedure adopted for the synthesis of the compliant structures and to evaluate the aerodynamic performances of the morphing wing. Nomenclature a = vector of CST extra-coefficients α = angle of attack [deg] α e = "effective" angle of attack [deg] c = airfoil chord [m] C d = drag coefficient for unit span C l = lift coefficient for unit span C m = pitch moment coefficient for unit span ∆κ = curvature difference function between the initial and the deformed shape [1/m] ∆L = length difference function between the initial and the deformed shape [m] δ LE = leading edge equivalent deflection [deg] δ T E = trailing edge equivalent deflection [deg] ψ = non-dimensional airfoil chordwise coordinate T p = CST-Vandermonde matrix of order p σ axial = axial stress due to the skin length variation [Pa]σ bend = bending stress due to the skin curvature variation [Pa]

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Section: Design Manufacturing and Wind Tunnel Test Of A Morphing Winmentioning

confidence: 99%

Design, Manufacturing and Wind Tunnel Validation of a Morphing Compliant Wing

Gaspari

Riccobene

Ricci

2018

Journal of Aircraft

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“…5 The main advantage of actively modifying the wing shape using a morphing technique is that an optimal shape for the wing and/or airfoil can be provided for different performance improvement objectives and during each distinct phase of aircraft flight, while preserving suitably smooth shapes, thus avoiding the off-design performance loss associated with single point optimized rigid shapes. 6 In addition to achieving important reductions in fuel consumption, adaptive, morphing wings can also be effectively used to replace conventional high-lift devices, 7,8 or the conventional control surfaces. 9 In recent years, a great interest has appeared for the development and application of morphing solutions on unmanned aerial vehicles (UAVs), because of increasingly greater efficiency requirements and of much simpler certification issues.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic performance improvement of the UAS-S4 Éhecatl morphing airfoil using novel optimization techniques

Gabor

Simon

Koreanschi

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, we present a morphing wing concept of the airfoil of the S4 unmanned aerial system, the new optimization methodology and the results obtained for multiple flight conditions. The reduction of the airfoil drag coefficient has been achieved using an in-house optimization tool based on the relatively new Artificial Bee Colony algorithm, coupled with the Broyden-Fletcher-Goldfarb-Shanno algorithm to provide a final refinement of the solution. A broad range of speeds and angles of attack have been studied. An advanced, multi-objective, commercially available optimizing tool was used to validate the proposed optimization strategy and the obtained results. The aerodynamic calculations were performed using the XFOIL solver, a two-dimensional linear panel method, coupled with an incompressible boundary layer model and a transition estimation criterion, to provide accurate estimations of the airfoil drag coefficient. Drag reductions of up to 14% have been achieved for a wide range of different flight conditions, using very small displacements of the airfoil surface, of only 2.5 mm.

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“…Morphing wings were used to adapt the wing span and airfoil camber [4,5] or the winglet's cant and toe angles [6], and to replace conventional high-lift devices [7,8], or the conventional control surfaces [9].…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation and wind tunnel tests investigation and validation of a morphing wing-tip demonstrator aerodynamic performance

Gabor

Koreanschi

Botez

et al. 2016

Aerospace Science and Technology

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/npsi/ctrl?action=rtdoc&an=21277526&lang=en http://nparc.cisti-icist.nrc-cnrc.gc.ca/npsi/ctrl?action=rtdoc&an=21277526&lang=fr READ THESE TERMS AND CONDITIONS CAREFULLY BEFORE USING THIS WEBSITE.http://nparc.cisti-icist.nrc-cnrc.gc.ca/npsi/jsp/nparc_cp.jsp?lang=en Vous avez des questions? Nous pouvons vous aider. Pour communiquer directement avec un auteur, consultez la première page de la revue dans laquelle son article a été publié afin de trouver ses coordonnées. Si vous n'arrivez pas à les repérer, communiquez avec nous à PublicationsArchive-ArchivesPublications@nrc-cnrc.gc.ca. Questions? Contact the NRC Publications Archive team atPublicationsArchive-ArchivesPublications@nrc-cnrc.gc.ca. If you wish to email the authors directly, please see the first page of the publication for their contact information. NRC Publications Archive Archives des publications du CNRCThis publication could be one of several versions: author's original, accepted manuscript or the publisher's version. / La version de cette publication peut être l'une des suivantes : la version prépublication de l'auteur, la version acceptée du manuscrit ou la version de l'éditeur. For the publisher's version, please access the DOI link below./ Pour consulter la version de l'éditeur, utilisez le lien DOI ci-dessous. This paper presents the results obtained from the numerical simulation and experimental wind tunnel testing of a morphing wing equipped with a flexible upper surface and controllable actuated aileron. The technology demonstrator is representative of a real aircraft wing tip section, and it was developed following a complex, multidisciplinary design process. The model was fitted with a composite material upper skin whose shape can be morphed, as a function of the flight condition, by four electrical actuators placed inside the wing structure. The optimizations were performed with the aim of controlling the extent of the laminar flow region, and the resulting shapes were scanned using high-precision photogrammetry. The numerical simulations were performed using Computational Fluid Dynamics (CFD) and included a model for predicting the laminar-to-turbulent flow transition over the entire wing surface. The analyses included cases with three aileron deflection angles and angles of attack situated within five degrees range. The CFD results were compared with infrared thermography measurements in terms of transition location, surface pressure measurements and balance loads measurements acquired during subsonic wind tunnel tests performed at the National Research Council Canada.

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Estimated performance of an adaptive trailing-edge device aimed at reducing fuel consumption on a medium-size aircraft

Cited by 29 publications

References 0 publications

Design, Manufacturing and Wind Tunnel Validation of a Morphing Compliant Wing

Design, Manufacturing and Wind Tunnel Validation of a Morphing Compliant Wing

Aerodynamic performance improvement of the UAS-S4 Éhecatl morphing airfoil using novel optimization techniques

Numerical simulation and wind tunnel tests investigation and validation of a morphing wing-tip demonstrator aerodynamic performance

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