Wing geometry as a tool for discrimination of Obsoletus group (Diptera: Ceratopogonidae: Culicoides) in France

ABSTRACT Unmanned Combat Aerial Vehicles (UCAVs) are believed by many to be the future of aerial strike/reconnaissance capability. This belief led to the design of the UCAV 1303 by Boeing Phantom Works and the US Airforce Lab in the late 1990s. Because UCAV 1303 is expected to take on a wide range of mission roles that are risky for human pilots, it needs to be highly adaptable. Geometric morphing can provide such adaptability and allow the UCAV 1303 to optimise its physical feature mid-flight to increase the lift-to-drag ratio, manoeuvrability, cruise distance, flight control, etc. This capability is extremely beneficial since it will enable the UCAV to reconcile conflicting mission requirements (e.g. loiter and dash within the same mission). In this study, we conduct several modifications to the wing geometry of UCAV 1303 via Computational Fluid Dynamics (CFD) to analyse its aerodynamic characteristics produced by a range of different wing geometric morphs. Here we look into two specific geometric morphing wings: linear twists on one of the wings and linear twists at both wings (wash-in and washout). A baseline CFD of the UCAV 1303 without any wing morphing is validated against published wind tunnel data, before proceeding to simulate morphing wing configurations. The results show that geometric morphing wing influences the UCAV-1303 aerodynamic characteristics significantly, improving the coefficient of lift and drag, pitching moment and rolling moment.

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Numerical and experimental validation of a morphed wing geometry using Price-Païdoussis wind-tunnel testing – CORRIGENDUM

The Aeronautical Journal ◽

10.1017/aer.2016.73 ◽

2016 ◽

Vol 120 (1230) ◽

pp. 1335-1335

Author(s):

R.M. Botez ◽

A. Koreanschi ◽

O. Sugar-Gabor

Keyword(s):

Wind Tunnel ◽

Experimental Validation ◽

Online Version ◽

Wind Tunnel Testing ◽

Correct Order ◽

Wing Geometry ◽

Tunnel Testing

The authors were listed incorrectly in the article by Botez(1). The authors should have appeared in the following order:A. Koreanschi, O. Sugar-Gabor and R.M. BotezThe article has now been updated with all authors listed in the correct order; this change has been made to the online version only.

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Temporal variation of wing geometry in Aedes albopictus

Memórias do Instituto Oswaldo Cruz ◽

10.1590/s0074-02762012000800011 ◽

2012 ◽

Vol 107 (8) ◽

pp. 1030-1034 ◽

Cited By ~ 24

Author(s):

Paloma Oliveira Vidal ◽

Eneas Carvalho ◽

Lincoln Suesdek

Keyword(s):

Temporal Variation ◽

Aedes Albopictus ◽

Wing Geometry

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Stability-based motion planning for a modular morphing wing

10.32920/ryerson.14655543 ◽

2021 ◽

Author(s):

Michael C. F. Kwong

Keyword(s):

Selection Process ◽

Static Stability ◽

Path Selection ◽

Critical Parameters ◽

Morphing Wing ◽

Wing Geometry ◽

Variable Geometry Truss ◽

Different Levels ◽

Longitudinal Static Stability

Aircraft wing geometry morphing is a technology that has seen recent interest due to demand for aircraft to improve aerodynamic performance for fuel saving. One proposed idea to alter wing geometry is by a modular morphing wing designed through a discretization method and constructed using variable geometry truss mechanisms (VGTM). For each morphing maneuver, there are sixteen possible actuation paths for each VGTM module, and thus offering a three module morphing wing to have a total of 16(to the power of 3) permutations of actuation paths for one morphing maneuver. Focused on longitudinal static stability, critical parameters and aircraft stability theory, this thesis proposes a method to find an optimal actuation path for a designated maneuver iteratively. A case study of a three module morphing wing demonstrated the actuation path selection process. Numerically, different actuation paths had different levels of longitudinal static stability; these paths were drawn in CATIA and were visually verified.

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Soaring and Gliding Flight of the Black Vulture

Journal of Experimental Biology ◽

10.1242/jeb.35.2.280 ◽

1958 ◽

Vol 35 (2) ◽

pp. 280-285

Author(s):

B. G. NEWMAN

Keyword(s):

Flow Separation ◽

Angle Of Attack ◽

High Angle ◽

High Angle Of Attack ◽

Wing Area ◽

Wing Span ◽

Gliding Flight ◽

Black Vulture ◽

Wing Geometry

1. The soaring and gliding performance of the black vulture has been analysed and the following conclusions are drawn. 2. The wing span of the bird is altered in flight so that it may perform two tasks efficiently. First, that it may soar in rising currents of air for which a low sinking speed and thus a large wing span are required. Secondly, that it may penetrate into wind without undue loss of height for which a reduced wing area is desirable. Adjustment of the wing geometry towards the optimum soaring configuration is achieved by bending forward and opening the primary tip feathers. 3. Since the airflow readily separates from the flat primary feathers at high angle of attack, these feathers, which are emarginated, are parted to form slots. The alula also presumably assists in delaying the flow separation over the primaries. 4. It is unlikely that the opening of the primaries reduces the vortex drag.

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Recent progress in flapping wings for micro aerial vehicle applications

Proceedings of the Institution of Mechanical Engineers Part C Journal of Mechanical Engineering Science ◽

10.1177/0954406220917426 ◽

2020 ◽

pp. 095440622091742

Author(s):

Naeem Haider ◽

Aamer Shahzad ◽

Muhammad Nafees Mumtaz Qadri ◽

Syed Irtiza Ali Shah

Keyword(s):

Leading Edge ◽

Flapping Wing ◽

Flapping Wings ◽

Structural Flexibility ◽

Micro Aerial Vehicles ◽

Flexible Wings ◽

Performance Variables ◽

Aerial Vehicles ◽

Wide Range ◽

Wing Geometry

Micro aerial vehicles using flapping wings are under investigation, as an alternative to fixed-wing and rotary-wing micro aerial vehicles. Such flapping-wing vehicles promise key potential advantages of high thrust, agility, and maneuverability, and have a wide range of applications. These applications include both military and commercial domains such as communication relay, search and rescue, visual reconnaissance, and field search. With the advancement in the computational sciences, developments in flapping-wing micro aerial vehicles have progressed exponentially. Such developments require a careful aerodynamic and aeroelastic design of the flapping wing. Therefore, aerodynamic tools are required to study such designs and configurations. In this paper, the role of several parameters is investigated, including the types of flapping wings, the effect of the kinematics and wing geometry (shape, configuration, and structural flexibility) on performance variables such as lift, drag, thrust, and efficiency in various modes of flight. Kinematic variables have a significant effect on the performance of the flapping wing. For instance, a high flap amplitude and pitch rotation, which supports the generation of the strong leading-edge vortex, generates higher thrust. Likewise, wing shape, configuration, and structural flexibility are shown to have a large impact on the performance of the flapping wing. The wing with optimum flexibility maximizes thrust where highly flexible wings lead to performance degradation due to change in the effective angle of attack. This study shows that the development of the flexible flapping wing with performance capabilities similar to those of natural fliers has not yet been achieved. Finally, opportunities for additional research in this field are recommended.

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