Log in

Relevant bibliographies by topics / Edge morphing / Journal articles

To see the other types of publications on this topic, follow the link: Edge morphing.

Journal articles on the topic 'Edge morphing'

Author: Grafiati

Published: 5 June 2025

Last updated: 2 August 2025

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 50 journal articles for your research on the topic 'Edge morphing.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse journal articles on a wide variety of disciplines and organise your bibliography correctly.

1

Communier, David, Ruxandra Mihaela Botez, and Tony Wong. "Design and Validation of a New Morphing Camber System by Testing in the Price—Païdoussis Subsonic Wind Tunnel." Aerospace 7, no. 3 (2020): 23. http://dx.doi.org/10.3390/aerospace7030023.

Full text

Abstract:

This paper presents the design and wind tunnel testing of a morphing camber system and an estimation of performances on an unmanned aerial vehicle. The morphing camber system is a combination of two subsystems: the morphing trailing edge and the morphing leading edge. Results of the present study show that the aerodynamics effects of the two subsystems are combined, without interfering with each other on the wing. The morphing camber system acts only on the lift coefficient at a 0° angle of attack when morphing the trailing edge, and only on the stall angle when morphing the leading edge. The

APA, Harvard, Vancouver, ISO, and other styles

2

Bashir, Musavir, Mir Hossein Negahban, Ruxandra Mihaela Botez, and Tony Wong. "Numerical Simulation of the Transient Flow around the Combined Morphing Leading-Edge and Trailing-Edge Airfoil." Biomimetics 9, no. 2 (2024): 109. http://dx.doi.org/10.3390/biomimetics9020109.

Full text

Abstract:

An integrated approach to active flow control is proposed by finding both the drooping leading edge and the morphing trailing edge for flow management. This strategy aims to manage flow separation control by utilizing the synergistic effects of both control mechanisms, which we call the combined morphing leading edge and trailing edge (CoMpLETE) technique. This design is inspired by a bionic porpoise nose and the flap movements of the cetacean species. The motion of this mechanism achieves a continuous, wave-like, variable airfoil camber. The dynamic motion of the airfoil’s upper and lower sur

APA, Harvard, Vancouver, ISO, and other styles

3

Zhang, Yaqing, Wenjie Ge, Ziang Zhang, Xiaojuan Mo, and Yonghong Zhang. "Design of compliant mechanism-based variable camber morphing wing with nonlinear large deformation." International Journal of Advanced Robotic Systems 16, no. 6 (2019): 172988141988674. http://dx.doi.org/10.1177/1729881419886740.

Full text

Abstract:

The morphing wing with large deformation can benefit its flight performance a lot in different conditions. In this study, a variable camber morphing wing with compliant leading and trailing edges is designed by large-displacement compliant mechanisms. The compliant mechanisms are carried out by a hyperelastic structure topology optimization, based on a nonlinear meshless method. A laminated leading-edge skin is designed to fit the curvature changing phenomenon of the leading edge during deformation. A morphing wing demonstrator was manufactured to testify its deformation capability. Comparing

APA, Harvard, Vancouver, ISO, and other styles

4

Zhang, Zhenkai, Alessandro De Gaspari, Sergio Ricci, Chen Song, and Chao Yang. "Gradient-Based Aerodynamic Optimization of an Airfoil with Morphing Leading and Trailing Edges." Applied Sciences 11, no. 4 (2021): 1929. http://dx.doi.org/10.3390/app11041929.

Full text

Abstract:

This article presents a gradient-based aerodynamic optimization framework and investigates optimum deformations for a transonic airfoil equipped with morphing leading and trailing edges. Specifically, the proposed optimization framework integrates an innovative morphing shape parameterization with a high fidelity Reynolds-averaged Navier–Stokes computational fluid dynamic solver, a hybrid mesh deformation algorithm, and an efficient gradient evaluation method based on continuous adjoint implementation. To achieve a feasible morphing shape, some structural properties of skin and wing-box constr

APA, Harvard, Vancouver, ISO, and other styles

5

Mao, Sen, Changchuan Xie, Lan Yang, and Chao Yang. "Static Aeroelastic Characteristics of Morphing Trailing-Edge Wing Using Geometrically Exact Vortex Lattice Method." International Journal of Aerospace Engineering 2019 (November 16, 2019): 1–15. http://dx.doi.org/10.1155/2019/5847627.

Full text

Abstract:

A morphing trailing-edge (TE) wing is an important morphing mode in aircraft design. In order to explore the static aeroelastic characteristics of a morphing TE wing, an efficient and feasible method for static aeroelastic analysis has been developed in this paper. A geometrically exact vortex lattice method (VLM) is applied to calculate the aerodynamic forces. Firstly, a typical model of a morphing TE wing is chosen and built which has an active morphing trailing edge driven by a piezoelectric patch. Then, the paper carries out the static aeroelastic analysis of the morphing TE wing and corre

APA, Harvard, Vancouver, ISO, and other styles

6

Xiang, Jinwu, Kai Liu, Daochun Li, Chunxiao Cheng, and Enlai Sha. "Unsteady aerodynamic characteristics of a morphing wing." Aircraft Engineering and Aerospace Technology 91, no. 1 (2018): 1–9. http://dx.doi.org/10.1108/aeat-04-2017-0101.

Full text

Abstract:

Purpose The purpose of this paper is to investigate the unsteady aerodynamic characteristics in the deflection process of a morphing wing with flexible trailing edge, which is based on time-accurate solutions. The dynamic effect of deflection process on the aerodynamics of morphing wing was studied. Design/methodology/approach The computational fluid dynamic method and dynamic mesh combined with user-defined functions were used to simulate the continuous morphing of the flexible trailing edge. The steady aerodynamic characteristics of the morphing deflection and the conventional deflection wer

APA, Harvard, Vancouver, ISO, and other styles

7

Communier, David, Franck Le Besnerais, Ruxandra Mihaela Botez, and Tony Wong. "Design, Manufacturing, and Testing of a New Concept for a Morphing Leading Edge using a Subsonic Blow Down Wind Tunnel." Biomimetics 4, no. 4 (2019): 76. http://dx.doi.org/10.3390/biomimetics4040076.

Full text

Abstract:

This paper presents the design and wind tunnel test results of a wing including a morphing leading edge for a medium unmanned aerial vehicle with a maximum wingspan of 5 m. The design of the morphing leading edge system is part of research on the design of a morphing camber system. The concept presented here has the advantage of being simple to manufacture (wooden construction) and light for the structure of the wing (compliance mechanism). The morphing leading edge prototype demonstrates the possibility of modifying the stall angle of the wing. In addition, the modification of the stall angle

APA, Harvard, Vancouver, ISO, and other styles

8

Kan, Zi, Daochun Li, Shiwei Zhao, Jinwu Xiang, and Enlai Sha. "Aeroacoustic and aerodynamic characteristics of a morphing airfoil." Aircraft Engineering and Aerospace Technology 93, no. 5 (2021): 888–99. http://dx.doi.org/10.1108/aeat-11-2020-0263.

Full text

Abstract:

Purpose This paper aims to assess the aeroacoustic and aerodynamic performance of a morphing airfoil with a flexible trailing edge (FTE). The objective is to make a comparison of the aerodynamic noise characteristics between the conventional airfoil with a flap and morphing airfoil and analyse the noise reduction mechanisms of the morphing airfoil. Design/methodology/approach The computational fluid dynamic method was used to calculate the aerodynamic coefficients of morphing airfoil and the Ffowcs-Williams and Hawking’s acoustic analogy methods were performed to predict the far-field noise of

APA, Harvard, Vancouver, ISO, and other styles

9

Cheng, Gui, Tianrui Ma, Jun Yang, Nan Chang, and Xiang Zhou. "Design and Experiment of a Seamless Morphing Trailing Edge." Aerospace 10, no. 3 (2023): 282. http://dx.doi.org/10.3390/aerospace10030282.

Full text

Abstract:

Morphing trailing edge wing as an important morphing wing technology has gained wide attention because of its advantages, such as gust mitigation, improved aerodynamic efficiency, and reduced radar reflective area. However, the key problems such as low load carrying capacity and insufficient smooth deformation profile are still not solved in a balanced manner. The purpose of this paper is to design a seamless morphing trailing edge structure that has good load bearing capacity and can realize a chord-wise camber variation with a smooth contour subjected to the required aerodynamic load. In thi

APA, Harvard, Vancouver, ISO, and other styles

10

Sodja, Jurij, Marcias J. Martinez, John C. Simpson, and Roeland De Breuker. "Experimental evaluation of a morphing leading edge concept." Journal of Intelligent Material Systems and Structures 30, no. 18-19 (2019): 2953–69. http://dx.doi.org/10.1177/1045389x19862369.

Full text

Abstract:

This article presents an experimental evaluation of a morphing leading edge demonstrator by investigating its morphed shape, the level of induced strains in the airfoil skin, the actuation force, and the morphing mechanism’s capability to lock and transfer the applied loads. In addition, a finite element model of the demonstrator is assembled comprising an elastic morphing skin and a kinematic morphing mechanism. The obtained results are used to assess whether the demonstrator performs according to the design objectives, such as the target shape, the character of the morphing deformation and t

APA, Harvard, Vancouver, ISO, and other styles

11

Kabir, A., A. S. M. Al-Obaidi, and F. W. Y. Myan. "Review and aerodynamic analysis of NACA 2415 morphing wing for variable span and scale morphing concepts using CFD analysis." Journal of Physics: Conference Series 2523, no. 1 (2023): 012033. http://dx.doi.org/10.1088/1742-6596/2523/1/012033.

Full text

Abstract:

Abstract Morphing wings made a significant advancement in aircraft engineering by improving aerodynamic performance for better fuel efficiency and are still under research. This paper reviewed and investigated some morphing wing types including the variable sweep, trailing edge, leading edge, variable span, variable chord, or scale, and airfoil morphing among others. Based on the review, two types of morphing wings were chosen for detailed investigation, and they were variable span and variable scale. Each morphing concept from the selected morphing wing types was implemented in airfoil wing c

APA, Harvard, Vancouver, ISO, and other styles

12

Zhou, Jin, and Shiwei Zhao. "Optimal design of watt six-bar transmission mechanism for morphing trailing edge." E3S Web of Conferences 268 (2021): 01077. http://dx.doi.org/10.1051/e3sconf/202126801077.

Full text

Abstract:

The morphing trailing edge could realize a continuous smooth deformation compared with conventional trailing edge, which effectively improves the aerodynamic performance. In this paper, a multi-step optimization design of watt six-bar transmission mechanism for morphing trailing edge is proposed. In the first optimization stage, the most effective aerodynamic shape and bar position in the middle of the morphing trailing edge is determined. In the second optimization stage, a watt six link transmission mechanism is proposed by using genetic algorithm to match the optimal shape from the first op

APA, Harvard, Vancouver, ISO, and other styles

13

Takahashi, Hiroki, Tomohiro Yokozeki, and Yoshiyasu Hirano. "Development of variable camber wing with morphing leading and trailing sections using corrugated structures." Journal of Intelligent Material Systems and Structures 27, no. 20 (2016): 2827–36. http://dx.doi.org/10.1177/1045389x16642298.

Full text

Abstract:

This article describes the development of variable camber morphing wing, which is mainly composed of corrugated structures. The morphing wing with both leading edge and trailing edge morphing sections is proposed and the prototype model is designed by consideration of finite element structural analysis with actuation mechanisms and aerodynamic analysis. Through wind tunnel experiment with the manufactured prototype model, smooth actuation without harmful deformation under 20 m/s airflow is demonstrated. The observed deformation shape is well correlated with simulated shape by analysis. Thereby

APA, Harvard, Vancouver, ISO, and other styles

14

Jia, Sijia, Zhenkai Zhang, Haibo Zhang, Chen Song, and Chao Yang. "Wind Tunnel Tests of 3D-Printed Variable Camber Morphing Wing." Aerospace 9, no. 11 (2022): 699. http://dx.doi.org/10.3390/aerospace9110699.

Full text

Abstract:

This paper introduces the realization and wind tunnel testing of a novel variable camber wing equipped with compliant morphing trailing edges. Based on the aerodynamic shape and compliant mechanisms that were optimized in advance, a wind tunnel model called mTE4 was developed, in which the rigid leading edge, rigid wing box, and compliant trailing edge were manufactured by 3D printing technology using three different materials. Due to difficulties in the detailed design of a small-scale model, special attention is devoted to the implementation procedure. Additionally, the static and dynamic ch

APA, Harvard, Vancouver, ISO, and other styles

15

Wang, C., H. Haddad Khodaparast, MI Friswell, et al. "Conceptual-level evaluation of a variable stiffness skin for a morphing wing leading edge." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 15 (2019): 5703–16. http://dx.doi.org/10.1177/0954410019855576.

Full text

Abstract:

A morphing leading edge produces a continuous aerodynamic surface that has no gaps between the moving and fixed parts. The continuous seamless shape has the potential to reduce drag, compared to conventional devices, such as slats that produce a discrete aerofoil shape change. However, the morphing leading edge has to achieve the required target shape by deforming from the baseline shape under the aerodynamic loads. In this paper, a conceptual-level method is proposed to evaluate the morphing leading edge structure. The feasibility of the skin design is validated by checking the failure index

APA, Harvard, Vancouver, ISO, and other styles

16

Tavares, Sérgio M. O., Pedro V. Gamboa, and Paulo M. S. T. de Castro. "Aircraft Wings and Morphing–Evolution of the Concepts." Encyclopedia 5, no. 3 (2025): 101. https://doi.org/10.3390/encyclopedia5030101.

Full text

Abstract:

This encyclopedia entry provides an updated appreciation of the evolution of morphing aircraft wings, organized as follows: first, lift concepts are briefly examined; second, patents related to lift enhancement are discussed, showcasing existing technology and its evolution; finally, several technologies for morphing wings and the role of UAVs as testbeds for many innovative concepts are highlighted. The background of morphing wings is presented through a recap of lift concepts and the presentation of representative patents that describe the evolution of leading-edge and trailing-edge devices,

APA, Harvard, Vancouver, ISO, and other styles

17

Huang, Doudou, and Louis Gagnon. "Relying on Dynamically Morphing Blades to Increase the Efficiency of a Cycloidal Rotor." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (2022): 012014. http://dx.doi.org/10.1088/1757-899x/1226/1/012014.

Full text

Abstract:

Abstract The configuration of the airfoil has a significant impact on its aerodynamic performance. This paper aims to improve the aerodynamic efficiency of the cycloidal rotor system by using dynamically morphing blades. Three different camber morphing concepts (leading edge deflection, trailing edge deformation and cambered NACA profile) have been applied to a baseline 2-bladed system with rotating and pitching NACA0015 aerofoils. Then, based on these camber concepts, 2D URANS numerical simulations were conducted for blades with different morphing degrees using OpenFOAM. The simulation result

APA, Harvard, Vancouver, ISO, and other styles

18

Lendraitis, Martynas. "Investigation of performance gains on a sailplane with morphing wing trailing edge." Mechanics 25, no. 4 (2019): 299–303. http://dx.doi.org/10.5755/j01.mech.25.4.22325.

Full text

Abstract:

Increasing the performance of a modern sailplane is challenging. Most of the known valid approaches have already been applied in practice. Morphing technology, which could allow to adapt to various flight stages is yet to be applied. An investigation of possible flight performance benefits of such technology is carried out here. Using a genetic algorithm, a morphing trailing edge flap for airfoil HQ-17 is formed for -4° and +12° flap deflections. The performance is evaluated and compared with a regular flap, which shows that for the HQ-17 airfoil, drag could be reduced by up to 36% in comparis

APA, Harvard, Vancouver, ISO, and other styles

19

Bashir, Musavir, Simon Longtin-Martel, Nicola Zonzini, Ruxandra Mihaela Botez, Alessandro Ceruti, and Tony Wong. "Optimization and Design of a Flexible Droop Nose Leading Edge Morphing Wing Based on a Novel Black Widow Optimization (B.W.O.) Algorithm—Part II." Designs 6, no. 6 (2022): 102. http://dx.doi.org/10.3390/designs6060102.

Full text

Abstract:

This work presents an aerodynamic and structural optimization for a Droop Nose Leading Edge Morphing airfoil as a high lift device for the UAS-S45. The results were obtained using three optimization algorithms: coupled Particle Swarm Optimization-Pattern Search, Genetic Algorithm, and Black Widow Optimization algorithm. The lift-to-drag ratio was used as the fitness function, and the impact of the choice of optimization algorithm selection on the fitness function was evaluated. The optimization was carried out at various Mach numbers of 0.08, 0.1, and 0.15, respectively, and at the cruise and

APA, Harvard, Vancouver, ISO, and other styles

20

Shi, Xintong, Yu Yang, Zhigang Wang, Sheng Zhang, Xiasheng Sun, and Wei Feng. "Design and Shape Monitoring of a Morphing Wing Trailing Edge." Aerospace 10, no. 2 (2023): 127. http://dx.doi.org/10.3390/aerospace10020127.

Full text

Abstract:

The morphing wing trailing edge is an attractive aviation structure due to its shape-adaptive ability, which can effectively improve the aerodynamic performance of an aircraft throughout the whole flight. In this paper, a mechanical solution for a variable camber trailing edge (VCTE) based on a multi-block rotating rib is proposed. Parametric optimizations are conducted to achieve the smooth and continuous deformation of the morphing rib. A prototype is designed according to the optimized results. In addition, the deformations of the trailing edge are monitored via an indirect method using a f

APA, Harvard, Vancouver, ISO, and other styles

21

Themistokleous, Charalampos, Nikolaos-Grigorios Markatos, John Prospathopoulos, Vasilis Riziotis, Giorgos Sieros, and George Papadakis. "A High-Lift Optimization Methodology for the Design of Leading and Trailing Edges on Morphing Wings." Applied Sciences 11, no. 6 (2021): 2822. http://dx.doi.org/10.3390/app11062822.

Full text

Abstract:

Morphing offers an attractive alternative compared to conventional hinged, multi-element high lift devices. In the present work, morphed shapes of a NACA 64A010 airfoil are optimized for maximum lift characteristics. Deformed shapes of the leading and trailing edge are represented through Bezier curves derived from locally defined control points. The optimization process employs the fast Foil2w in-house viscous-inviscid interaction solver for the calculation of aerodynamic characteristics. Transitional flow results indicate that combined leading and trailing edge morphing may increase maximum

APA, Harvard, Vancouver, ISO, and other styles

22

Abdessemed, Chawki, Abdessalem Bouferrouk, and Yufeng Yao. "Effects of an Unsteady Morphing Wing with Seamless Side-Edge Transition on Aerodynamic Performance." Energies 15, no. 3 (2022): 1093. http://dx.doi.org/10.3390/en15031093.

Full text

Abstract:

This paper presents an unsteady flow analysis of a 3D wing with a morphing trailing edge flap (TEF) and a seamless side-edge transition between the morphed and static parts of a wing by introducing an unsteady parametrization method. First, a 3D steady Reynolds-averaged Navier–Stokes (RANS) analysis of a statically morphed TEF with seamless transition is performed and the results are compared with both a baseline clean wing and a wing with a traditional hinged flap configuration at a Reynolds number of 0.7 × 106 for a range of angles of attack (AoA), from 4° to 15°. This study extends some pre

APA, Harvard, Vancouver, ISO, and other styles

23

Negahban, Mir Hossein, Alexandre Hallonet, Marie Noupoussi Woumeni, Constance Nguyen, and Ruxandra Mihaela Botez. "Structural and Topological Optimization of a Novel Elephant Trunk Mechanism for Morphing Wing Applications." Aerospace 12, no. 5 (2025): 381. https://doi.org/10.3390/aerospace12050381.

Full text

Abstract:

A novel mechanism for seamless morphing trailing edge flaps is presented in this paper. This bio-inspired morphing concept is derived from an elephant’s trunk and is called the Elephant Trunk Mechanism (ETM). The structural flexibility of an elephant’s trunk and its ability to perform various types of deformations make it a promising choice in morphing technology for increasing the performance of continuous and smooth downward bending deformation at a trailing edge. This mechanism consists of a number of tooth-like elements attached to a solid wing box; the contractions of these tooth-like ele

APA, Harvard, Vancouver, ISO, and other styles

24

Viola, Ignazio Maria, Gabriele Pisetta, Weidong Dai, Abel Arredondo-Galeana, Anna Young, and Amanda Smyth. "Morphing Blades." International Marine Energy Journal 5, no. 2 (2022): 183–93. http://dx.doi.org/10.36688/imej.5.183-193.

Full text

Abstract:

Tidal turbines experience large load fluctuations due to the unsteady environment and the shear in the tidal flow. Mitigating these fluctuations without affecting the mean load would result in lower capital and operational costs. In this paper we discuss how this could be achieved through blades that passively and elastically adapt their camber and angle of attack to counteract unsteady flow conditions. Firstly, we discuss the underlying principles of unsteady thrust mitigation. We show that complete cancellation of the thrust fluctuations would be possible if every blade section could pitch p

APA, Harvard, Vancouver, ISO, and other styles

25

Wang, Yuanjing, Pengxuan Lei, Binbin Lv, Yuchen Li, and Hongtao Guo. "Study on Fluid–Structure Interaction of a Camber Morphing Wing." Vibration 6, no. 4 (2023): 1060–74. http://dx.doi.org/10.3390/vibration6040062.

Full text

Abstract:

The influence of trailing edge deformation on the aerodynamic characteristics of camber morphing wings is an important topic in the aviation field. In this paper, a new memory alloy actuator is proposed to realize trailing edge deformation, and computational fluid dynamics (CFD) and wind tunnel experiments are used to study the influence of trailing edge deformation on the aerodynamic characteristics of the camber morphing wings. The experiments was carried out in a transonic wind tunnel with Mach numbers ranging from 0.4 to 0.8 and angles of attack ranging from 0° to 6°. The external flow fie

APA, Harvard, Vancouver, ISO, and other styles

26

Wang, Zhigang, and Yu Yang. "Design of a Variable-Stiffness Compliant Skin for a Morphing Leading Edge." Applied Sciences 11, no. 7 (2021): 3165. http://dx.doi.org/10.3390/app11073165.

Full text

Abstract:

A seamless and smooth morphing leading edge has remarkable potential for noise abatement and drag reduction of civil aircraft. Variable-stiffness compliant skin based on tailored composite laminate is a concept with great potential for morphing leading edge, but the currently proposed methods have difficulty in taking the manufacturing constraints or layup sequence into account during the optimization process. This paper proposes an innovative two-step design method for a variable-stiffness compliant skin of a morphing leading edge, which includes layup optimization and layup adjustment. The c

APA, Harvard, Vancouver, ISO, and other styles

27

Jodin, Gurvan, Johannes Scheller, Eric Duhayon, Jean François Rouchon, and Marianna Braza. "Implementation of a Hybrid Electro-Active Actuated Morphing Wing in Wind Tunnel." Solid State Phenomena 260 (July 2017): 85–91. http://dx.doi.org/10.4028/www.scientific.net/ssp.260.85.

Full text

Abstract:

Amongst current aircraft research topics, morphing wing is of great interest for improving the aerodynamic performance. A morphing wing prototype has been designed for wind tunnel experiments. The rear part of the wing - corresponding to the retracted flap - is actuated via a hybrid actuation system using both low frequency camber control and a high frequency vibrating trailing edge. The camber is modified via surface embedded shape memory alloys. The trailing edge vibrates thanks to piezoelectric macro-fiber composites. The actuated camber, amplitude and frequency ranges are characterized. To

APA, Harvard, Vancouver, ISO, and other styles

28

Mounir Nour-Allah Kouchlef and Shen Xing. "Development of a fishbone camber morphing airfoil actuated by SMA wires." International Journal of Science and Research Archive 12, no. 2 (2024): 800–808. http://dx.doi.org/10.30574/ijsra.2024.12.1.0900.

Full text

Abstract:

This paper investigates the design and aerodynamic efficiency of a bio-inspired variable camber morphing airfoil featuring NACA0012 ribs with a deformable fishbone trailing edge. The deformation mechanism uses smart memory alloy wires arranged on the ribs to deflect the trailing edge upwards or downwards based on the set of wires actuated. Experimental validation of the designed system demonstrates two distinct angles up to 30 degrees. Subsequent aerodynamic investigations were conducted to compare the performance of the morphing trailing edge concept with conventional flap configurations. Res

APA, Harvard, Vancouver, ISO, and other styles

29

Pecora, R., M. Magnifico, F. Amoroso, and E. Monaco. "Multi-parametric flutter analysis of a morphing wing trailing edge." Aeronautical Journal 118, no. 1207 (2014): 1063–78. http://dx.doi.org/10.1017/s000192400000974x.

Full text

Abstract:

Abstract The development of adaptive morphing wings has been individuated as one of the crucial topics in the greening of the next generation air transport. Research programs are currently running worldwide to exploit the potentiality of morphing concepts in the optimisation of aircraft efficiency and in the consequent reduction of fuel burn. Among these, SARISTU represents the largest European funded research project which ambitiously addresses the challenges posed by the physical integration of smart concepts in real aircraft structures; for the first time ever, SARISTU will experimentally d

APA, Harvard, Vancouver, ISO, and other styles

30

NEGAHBAN, Mir Hossein, and Ruxandra Mihaela BOTEZ. "Comparison of Aerodynamic Characteristics of Morphing and Conventional Wings." INCAS BULLETIN 17, no. 2 (2025): 47–58. https://doi.org/10.13111/2066-8201.2025.17.2.5.

Full text

Abstract:

The present research investigates the advantages of a morphing versus a hinged flap. The morphing wing model is equipped with a morphing trailing edge, while the conventional wing has a hinged flap system. The aerodynamic and fight dynamics characteristics of both wings are evaluated, and a comparison is drawn to find out how the morphing wing enhances the flight performance in cruise flight conditions in terms of flight range increase. For this purpose, gradient-based aerodynamic optimization is performed to find the ideal configuration of a morphing flap in a cruise flight with the objective

APA, Harvard, Vancouver, ISO, and other styles

31

Klimczyk, Witold Artur, and Zdobyslaw Jan Goraj. "Analysis and optimization of morphing wing aerodynamics." Aircraft Engineering and Aerospace Technology 91, no. 3 (2019): 538–46. http://dx.doi.org/10.1108/aeat-12-2017-0289.

Full text

Abstract:

PurposeThe purpose of this paper is to present a method for analysis and optimization of morphing wing. Moreover, a numerical advantage of morphing airfoil wing, typically assessed in simplified two-dimensional analysis is found using higher fidelity methods.Design/methodology/approachBecause of multi-point nature of morphing wing optimization, an approach for optimization by analysis is presented. Starting from naïve parametrization, multi-fidelity aerodynamic data are used to construct response surface model. From the model, many significant information are extracted related to parameters ef

APA, Harvard, Vancouver, ISO, and other styles

32

Neogi, Ishan, Vardhan Niral Shah, Pragalbh Dev Singh, and Vaibhav Joshi. "Propulsion of a combined heaving and trailing-edge morphing foil for bio-inspired applications." Physics of Fluids 35, no. 4 (2023): 043610. http://dx.doi.org/10.1063/5.0145443.

Full text

Abstract:

Locomotion of aquatic animals involves flapping of their body to generate lift and thrust. Through evolution, they have mastered their ability to move through complex environments in an energy-efficient manner. A crucial component of this movement is the ability to actively bend their bodies to generate maximum thrust. This motion is widely termed as morphing. A simplification of this motion is implemented for a foil in this study to realize a thrust-generating bio-inspired device. The propulsive performance of the heaving foil undergoing a prescribed trailing-edge morphing is numerically stud

APA, Harvard, Vancouver, ISO, and other styles

33

Ameduri, Salvatore. "A SMA Based Morphing Leading Edge Architecture." Advanced Materials Research 1016 (August 2014): 383–88. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.383.

Full text

Abstract:

This paper analyses a morphing leading edge device, activated by a Shape Memory Alloy (SMA) actuator. The objective is to achieve the Droop Nose effect for particular phases of the flight (e.g. take-off, landing), both obtaining an increased lift and preserving the laminar flow. The device is constituted of: a kinematic chain at the level of the wing section, transmitting motion to the skin, this way fitting the Droop Nose target shape; a span-wise architecture integrated with a SMA actuator, ensuring both a reduction of the actuation forces and the balancing of the aerodynamic external load.

APA, Harvard, Vancouver, ISO, and other styles

34

De Gaspari, Alessandro, and Frédéric Moens. "Aerodynamic Shape Design and Validation of an Advanced High-Lift Device for a Regional Aircraft with Morphing Droop Nose." International Journal of Aerospace Engineering 2019 (March 27, 2019): 1–21. http://dx.doi.org/10.1155/2019/7982168.

Full text

Abstract:

In the present work, the aerodynamic shape design of an advanced high-lift system for a natural laminar flow (NLF) wing, based on the combination of a morphing droop nose and a single slot trailing edge flap, is presented. The paper presents both the aerodynamic design and optimization of the NLF wing and the high-lift configuration considering the mutual effects of both flap devices. Concerning the morphing droop nose (DN), after defining the parameterization techniques adopted to describe the geometry in terms of morphing shape and flap settings, the external configuration is obtained by an

APA, Harvard, Vancouver, ISO, and other styles

35

Jensen, Peter Dørffler Ladegaard, Fengwen Wang, Ignazio Dimino, and Ole Sigmund. "Topology Optimization of Large-Scale 3D Morphing Wing Structures." Actuators 10, no. 9 (2021): 217. http://dx.doi.org/10.3390/act10090217.

Full text

Abstract:

This work proposes a systematic topology optimization approach for simultaneously designing the morphing functionality and actuation in three-dimensional wing structures. The actuation was modeled by a linear-strain-based expansion in the actuation material. A three-phase material model was employed to represent structural and actuating materials and voids. To ensure both structural stiffness with respect to aerodynamic loading and morphing capabilities, the optimization problem was formulated to minimize structural compliance, while the morphing functionality was enforced by constraining a mo

APA, Harvard, Vancouver, ISO, and other styles

36

Magrini, Andrea, Ernesto Benini, Rita Ponza, et al. "Comparison of Constrained Parameterisation Strategies for Aerodynamic Optimisation of Morphing Leading Edge Airfoil." Aerospace 6, no. 3 (2019): 31. http://dx.doi.org/10.3390/aerospace6030031.

Full text

Abstract:

In the context of ambitious targets for reducing environmental impact in the aviation sector, dictated by international institutions, morphing aircraft are expected to have potential for achieving the required efficiency increases. However, there are still open issues related to the design and implementation of deformable structures. In this paper, we compare three constrained parameterisation strategies for the aerodynamic design of a morphing leading edge, representing a potential substitute for traditional high-lift systems. In order to facilitate the structural design and promote the feasi

APA, Harvard, Vancouver, ISO, and other styles

37

Kumar, Ravi, and Santanu Ghosh. "Aerodynamic Impacts of Convergent Slot Implementation on Hinged and Morphed NACA 0012 Airfoil Operating at a High Reynolds Number." Defence Science Journal 75, no. 1 (2025): 3–9. https://doi.org/10.14429/dsj.75.19883.

Full text

Abstract:

Trailing-edge modifications on the NACA 0012 airfoil for lift enhancement are numerically investigated at a Reynolds number 4.58×106. Specifically, three variations in the trailing-edge geometry are tested: a hinged flap with hinge location at 70 % of chord, and two variations of continuous camber-morphed trailing edge: from 70 % chord to 100 % chord and from 70 % chord to 90 % chord. Reynolds-Averaged Navier-Stokes (RANS) simulations are performed using ANSYS Fluent with Menter’s SST k-ω two-equation turbulence model. Predictions of aerodynamic characteristics reveal that the continuous morph

APA, Harvard, Vancouver, ISO, and other styles

38

Kumar, Ravi, and Santanu Ghosh. "Aerodynamic Impacts of Convergent Slot Implementation on Hinged and Morphed NACA 0012 Airfoil Operating at a High Reynolds Number." Defence Science Journal 75, no. 1 (2025): 3–9. https://doi.org/10.14429/dsj.19883.

Full text

Abstract:

Trailing-edge modifications on the NACA 0012 airfoil for lift enhancement are numerically investigated at a Reynolds number 4.58×106. Specifically, three variations in the trailing-edge geometry are tested: a hinged flap with hinge location at 70 % of chord, and two variations of continuous camber-morphed trailing edge: from 70 % chord to 100 % chord and from 70 % chord to 90 % chord. Reynolds-Averaged Navier-Stokes (RANS) simulations are performed using ANSYS Fluent with Menter’s SST k-ω two-equation turbulence model. Predictions of aerodynamic characteristics reveal that the continuous morph

APA, Harvard, Vancouver, ISO, and other styles

39

Rudenko, Anton, André Hannig, Hans Peter Monner, and Peter Horst. "Extremely deformable morphing leading edge: Optimization, design and structural testing." Journal of Intelligent Material Systems and Structures 29, no. 5 (2017): 764–73. http://dx.doi.org/10.1177/1045389x17721036.

Full text

Abstract:

The future generation of high-lift devices needs to be improved to reduce the noise footprint and increase the performance for takeoff and landing of transport aircraft. To contribute to these goals, an active blown Coandă flap-based high-lift system is being investigated within the German national Collaborative Research Center 880 as an alternative to the state-of-the-art flaps. A key part of this system is an adaptive gapless droop nose with extremely large morphing deformation. The design and construction of this component are based on a structural optimization framework. The framework cons

APA, Harvard, Vancouver, ISO, and other styles

40

Moens. "Augmented Aircraft Performance with the Use of Morphing Technology for a Turboprop Regional Aircraft Wing." Biomimetics 4, no. 3 (2019): 64. http://dx.doi.org/10.3390/biomimetics4030064.

Full text

Abstract:

This article presents some application of the morphing technology for aerodynamic performance improvement of turboprop regional aircraft. It summarizes the results obtained in the framework of the Clean Sky 2 AIRGREEN2 program for the development and application of dedicated morphing devices for take-off and landing, and their uses in off design conditions. The wing of the reference aircraft configuration considers Natural Laminar Flow (NLF) characteristics. A deformable leading edge morphing device (“droop nose”) and a multi-functional segmented flap system have been considered. For the droop

APA, Harvard, Vancouver, ISO, and other styles

41

Dharmdas, Alexsteven, Arun Y. Patil, Azar Baig, et al. "An Experimental and Simulation Study of the Active Camber Morphing Concept on Airfoils Using Bio-Inspired Structures." Biomimetics 8, no. 2 (2023): 251. http://dx.doi.org/10.3390/biomimetics8020251.

Full text

Abstract:

Birds are capable of morphing their wings across different flight modes and speeds to improve their aerodynamic performance. In light of this, the study aims to investigate a more optimized solution compared to conventional structural wing designs. The design challenges faced by the aviation industry today require innovative techniques to improve flight efficiency and minimize environmental impact. This study focuses on the aeroelastic impact validation of wing trailing edge morphing, which undergoes significant structural changes to enhance performance as per mission requirements. The approac

APA, Harvard, Vancouver, ISO, and other styles

42

Ferrier, L., M. Vezza, and H. Zare-Behtash. "Improving the aerodynamic performance of a cycloidal rotor through active compliant morphing." Aeronautical Journal 121, no. 1241 (2017): 901–15. http://dx.doi.org/10.1017/aer.2017.34.

Full text

Abstract:

ABSTRACTCycloidal rotors are a novel form of propulsion system that can be adapted to various forms of transport such as air and marine vehicles, with a geometrical design differing significantly from the conventional screw propeller. Research on cycloidal rotor design began in the early 1930s and has developed throughout the years to the point where such devices now operate as propulsion systems for various aerospace applications such as micro air vehicles, unmanned air vehicles and compound helicopters. The majority of research conducted on the cycloidal rotor’s aerodynamic performance have

APA, Harvard, Vancouver, ISO, and other styles

43

Lendraitis, Martynas, and Vaidas Lukoševičius. "Novel Approach of Airfoil Shape Representation Using Modified Finite Element Method for Morphing Trailing Edge." Mathematics 11, no. 9 (2023): 1986. http://dx.doi.org/10.3390/math11091986.

Full text

Abstract:

This study presents a novel approach to parameterize the geometry of a morphing trailing-edge flap that allows its aerodynamics to be optimized while capturing the expected structural behavior of the flap. This approach is based on the finite frame element method, whereby the initial flap surface is defined as a structure with constraints that are similar to those of a morphing flap with passive skin. The initial shape is modified by placing a series of distributed loads on the surface. The finite frame element method is modified with rigid rotation corrections to maintain the initial element

APA, Harvard, Vancouver, ISO, and other styles

44

Abdessemed, Chawki, Yufeng Yao, and Abdessalem Bouferrouk. "Near Stall Unsteady Flow Responses to Morphing Flap Deflections." Fluids 6, no. 5 (2021): 180. http://dx.doi.org/10.3390/fluids6050180.

Full text

Abstract:

The unsteady flow characteristics and responses of an NACA 0012 airfoil fitted with a bio-inspired morphing trailing edge flap (TEF) at near-stall angles of attack (AoA) undergoing downward deflections are investigated at a Reynolds number of 0.62 × 106 near stall. An unsteady geometric parametrization and a dynamic meshing scheme are used to drive the morphing motion. The objective is to determine the susceptibility of near-stall flow to a morphing actuation and the viability of rapid downward flap deflection as a control mechanism, including its effect on transient forces and flow field unst

APA, Harvard, Vancouver, ISO, and other styles

45

De Gaspari, Alessandro, and Sergio Ricci. "Knowledge-Based Shape Optimization of Morphing Wing for More Efficient Aircraft." International Journal of Aerospace Engineering 2015 (2015): 1–19. http://dx.doi.org/10.1155/2015/325724.

Full text

Abstract:

An optimization procedure for the shape design of morphing aircraft is presented. The process is coupled with a knowledge-based framework combining parametric geometry representation, multidisciplinary modelling, and genetic algorithm. The parameterization method exploits the implicit properties of the Bernstein polynomial least squares fitting to allow both local and global shape control. The framework is able to introduce morphing shape changes in a feasible way, taking into account the presence of structural parts, such as the wing-box, the physical behaviour of the morphing skins, and the

APA, Harvard, Vancouver, ISO, and other styles

46

Feraru, Mădălin-Dorin, Daniel Măriuța, Marius Stoia-Djeska, and Lucian-Teodor Grigorie. "Numerical Investigation of an NACA 13112 Morphing Airfoil." Biomimetics 9, no. 10 (2024): 635. http://dx.doi.org/10.3390/biomimetics9100635.

Full text

Abstract:

This article presents a numerical study on the 2D aerodynamic characteristics of an airfoil with a morphed camber. The operational regime of the main rotor blade of the IAR 330 PUMA helicopter was encompassed in CFD simulations, performed over an angle of attack range of α=[−3°; 18°], and a Mach number of M=0.38. Various degrees of camber adjustment were smoothly implemented to the trailing-edge section of the NACA13112 airfoil, with a corresponding chord length of c=600 mm at the Reynolds number, Re=5.138×106, and the resulting changes in static lift and drag were calculated. The study examin

APA, Harvard, Vancouver, ISO, and other styles

47

Arena, Maurizio, Christof Nagel, Rosario Pecora, Oliver Schorsch, Antonio Concilio, and Ignazio Dimino. "Static and Dynamic Performance of a Morphing Trailing Edge Concept with High-Damping Elastomeric Skin." Aerospace 6, no. 2 (2019): 22. http://dx.doi.org/10.3390/aerospace6020022.

Full text

Abstract:

Nature has many striking examples of adaptive structures: the emulation of birds’ flight is the true challenge of a morphing wing. The integration of increasingly innovative technologies, such as reliable kinematic mechanisms, embedded servo-actuation and smart materials systems, enables us to realize new structural systems fully compatible with the more and more stringent airworthiness requirements. In this paper, the authors describe the characterization of an adaptive structure, representative of a wing trailing edge, consisting of a finger-like rib mechanism with a highly deformable skin,

APA, Harvard, Vancouver, ISO, and other styles

48

Wu, R., C. Soutis, S. Zhong, and A. Filippone. "A morphing aerofoil with highly controllable aerodynamic performance." Aeronautical Journal 121, no. 1235 (2016): 54–72. http://dx.doi.org/10.1017/aer.2016.113.

Full text

Abstract:

ABSTRACTIn this paper, a morphing carbon fibre composite aerofoil concept with an active trailing edge is proposed. This aerofoil features of camber morphing with multiple degrees of freedom. The shape morphing is enabled by an innovative structure driven by an electrical actuation system that uses linear ultrasonic motors (LUSM) with compliant runners, enabling full control of multiple degrees of freedom. The compliant runners also serve as structural components that carry the aerodynamic load and maintain a smooth skin curvature. The morphing structure with compliant truss is shown to exhibi

APA, Harvard, Vancouver, ISO, and other styles

49

Stevens, Tyler R., Nathan B. Crane, and Rydge B. Mulford. "Topology Morphing Insulation: A Review of Technologies and Energy Performance in Dynamic Building Insulation." Energies 16, no. 19 (2023): 6978. http://dx.doi.org/10.3390/en16196978.

Full text

Abstract:

Topology morphing insulation enables the on-demand switching of thermal properties between insulative and conducting states through shape change. The adaptive nature of these systems allows them to regulate heat transfer by dynamically altering insulation materials or systems in response to changing conditions, including environmental factors, electrical grid dynamics, and occupant requirements. In this article, we highlight the potential of topology morphing insulation for advancing building envelope design, improving energy efficiency, and facilitating on-demand adjustments in effective ther

APA, Harvard, Vancouver, ISO, and other styles

50

Li, Daochun, Qichen Liu, Yining Wu, and Jinwu Xiang. "Design and analysis of a morphing drag rudder on the aerodynamics, structural deformation, and the required actuating moment." Journal of Intelligent Material Systems and Structures 29, no. 6 (2017): 1038–49. http://dx.doi.org/10.1177/1045389x17730910.

Full text

Abstract:

The split drag rudder is an important yawing control device for the tailless flying-wing aircraft. In this article, a new morphing drag rudder is proposed based on the chordwise continuous variable camber technology. The designs of the structure and actuation system are first presented. A comparative study on the aerodynamics of the morphing and traditional drag rudders is performed numerically. The results show that the morphing drag rudder experiences a larger aerodynamic drag than the traditional one at small angles of attack. The analysis on the structural deformation and the required actu

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!