Relevant bibliographies by topics / Wings

Academic literature on the topic 'Wings'

Author: Grafiati
Published: 4 June 2021
Last updated: 29 July 2024

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Journal articles on the topic "Wings"

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Harbig, R. R., J. Sheridan, and M. C. Thompson. "Relationship between aerodynamic forces, flow structures and wing camber for rotating insect wing planforms." Journal of Fluid Mechanics 730 (July 30, 2013): 52–75. http://dx.doi.org/10.1017/jfm.2013.335.

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AbstractWing deformation is observed during the flight of some insect species; however, the effect of these distorted wing shapes on the leading edge vortex (LEV) is not well understood. In this study, we investigate the effect of one of these deformation parameters, (rigid) wing camber, on the flow structures and aerodynamic forces for insect-like wings, using a numerical model of an altered fruit fly wing revolving at a constant angular velocity. Both positive and negative camber was investigated at Reynolds numbers of 120 and 1500, along with the chordwise location of maximum camber. It was found that negatively cambered wings produce very similar LEV structures to non-cambered wings at both Reynolds numbers, but high positive camber resulted in the formation of multiple streamwise vortices at the higher Reynolds number, which disrupt the development of the main LEV. Despite this, positively cambered wings were found to produce higher lift to drag ratios than flat or negatively cambered wings. It was determined that a region of low pressure near the wing’s leading edge, combined with the curvature of the wing’s upper surface in this region, resulted in a vertical tilting of the net force vector for positively cambered wings, which explains how insects can benefit from wing camber.
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Dao, Thanh Tien, Thi Kim Loan Au, Soo Hyung Park, and Hoon Cheol Park. "Effect of Wing Corrugation on the Aerodynamic Efficiency of Two-Dimensional Flapping Wings." Applied Sciences 10, no. 20 (October 21, 2020): 7375. http://dx.doi.org/10.3390/app10207375.

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Many previous studies have shown that wing corrugation of an insect wing is only structurally beneficial in enhancing the wing’s bending stiffness and does not much help to improve the aerodynamic performance of flapping wings. This study uses two-dimensional computational fluid dynamics (CFD) in aiming to identify a proper wing corrugation that can enhance the aerodynamic performance of the KUBeetle, an insect-like flapping-wing micro air vehicle (MAV), which operates at a Reynolds number of less than 13,000. For this purpose, various two-dimensional corrugated wings were numerically investigated. The two-dimensional flapping wing motion was extracted from the measured three-dimensional wing kinematics of the KUBeetle at spanwise locations of r = (0.375 and 0.75)R. The CFD analysis showed that at both spanwise locations, the corrugations placed over the entire wing were not beneficial for improving aerodynamic efficiency. However, for the two-dimensional flapping wing at the spanwise location of r = 0.375R, where the wing experiences relatively high angles of attack, three specially designed wings with leading-edge corrugation showed higher aerodynamic performance than that of the non-corrugated smooth wing. The improvement is closely related to the flow patterns formed around the wings. Therefore, the proposed leading-edge corrugation is suggested for the inboard wing of the KUBeetle to enhance aerodynamic performance. The corrugation in the inboard wing may also be structurally beneficial.
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Medved, Victor, James H. Marden, Howard W. Fescemyer, Joshua P. Der, Jin Liu, Najmus Mahfooz, and Aleksandar Popadić. "Origin and diversification of wings: Insights from a neopteran insect." Proceedings of the National Academy of Sciences 112, no. 52 (December 14, 2015): 15946–51. http://dx.doi.org/10.1073/pnas.1509517112.

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Winged insects underwent an unparalleled evolutionary radiation, but mechanisms underlying the origin and diversification of wings in basal insects are sparsely known compared with more derived holometabolous insects. In the neopteran species Oncopeltus fasciatus, we manipulated wing specification genes and used RNA-seq to obtain both functional and genomic perspectives. Combined with previous studies, our results suggest the following key steps in wing origin and diversification. First, a set of dorsally derived outgrowths evolved along a number of body segments including the first thoracic segment (T1). Homeotic genes were subsequently co-opted to suppress growth of some dorsal flaps in the thorax and abdomen. In T1 this suppression was accomplished by Sex combs reduced, that when experimentally removed, results in an ectopic T1 flap similar to prothoracic winglets present in fossil hemipteroids and other early insects. Global gene-expression differences in ectopic T1 vs. T2/T3 wings suggest that the transition from flaps to wings required ventrally originating cells, homologous with those in ancestral arthropod gill flaps/epipods, to migrate dorsally and fuse with the dorsal flap tissue thereby bringing new functional gene networks; these presumably enabled the T2/T3 wing’s increased size and functionality. Third, “fused” wings became both the wing blade and surrounding regions of the dorsal thorax cuticle, providing tissue for subsequent modifications including wing folding and the fit of folded wings. Finally, Ultrabithorax was co-opted to uncouple the morphology of T2 and T3 wings and to act as a general modifier of hindwings, which in turn governed the subsequent diversification of lineage-specific wing forms.
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Harbig, R. R., J. Sheridan, and M. C. Thompson. "The role of advance ratio and aspect ratio in determining leading-edge vortex stability for flapping flight." Journal of Fluid Mechanics 751 (June 16, 2014): 71–105. http://dx.doi.org/10.1017/jfm.2014.262.

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AbstractThe effects of advance ratio and the wing’s aspect ratio on the structure of the leading-edge vortex (LEV) that forms on flapping and rotating wings under insect-like flight conditions are not well understood. However, recent studies have indicated that they could play a role in determining the stable attachment of the LEV. In this study, a numerical model of a flapping wing at insect Reynolds numbers is used to explore the effects of these parameters on the characteristics and stability of the LEV. The word ‘stability’ is used here to describe whether the LEV was attached throughout the stroke or if it was shed. It is demonstrated that increasing the advance ratio enhances vorticity production at the leading edge during the downstroke, and this results in more rapid growth of the LEV for non-zero advance ratios. Increasing the wing aspect ratio was found to have the effect of shortening the wing’s chord length relative to the LEV’s size. These two effects combined determine the stability of the LEV. For high advance ratios and large aspect ratios, the LEV was observed to quickly grow to envelop the entire wing during the early stages of the downstroke. Continued rotation of the wing resulted in the LEV being eventually shed as part of a vortex loop that peels away from the wing’s tip. The shedding of the LEV for high-aspect-ratio wings at non-zero advance ratios leads to reduced aerodynamic performance of these wings, which helps to explain why a number of insect species have evolved to have low-aspect-ratio wings.
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DWIVEDI, Y. D., ABHISHEK MOHAPATRA, T. BLESSINGTON, and Md IRFAN. "Experimental Flow Field Investigation of the Bio-Inspired Corrugated Wing for MAV Applications." INCAS BULLETIN 13, no. 2 (June 4, 2021): 37–50. http://dx.doi.org/10.13111/2066-8201.2021.13.2.5.

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This is an experimental flow field study of a bio-inspired corrugated finite wing from the dragonfly intended to assess the flow behavior over the wing and compare it with a wing of the same geometry with filled corrugation, at low Reynolds numbers 46000 and 67000. The work purpose is to explore the potential application of such types of wings for Micro Air Vehicles (MAVs) or micro sized Unmanned Air Vehicles (UAVs). Two types of wings are taken into account: first wing was a bio-inspired corrugated wing which was obtained from the mid span of the dragonfly, and the second wing was the same geometry with filled corrugation. Both wings were fabricated by using 3-D printing machine. The tufts were glued at three different locations i.e. at center, 30%, and 60% of the semi-span towards the right side of the wing at the trailing edge. The boundary layers were measured by using boundary layer rakes inside the open-end low speed wing tunnel with varied angles of attack. The results of the tuft flow visualization showed that the flow pattern at different span locations was different at different angles of attack and different wing velocities (Reynolds number). The fluctuations of the two different wings at the same angle of attack and Reynolds number were found different. Also, the directions of the flow for both wings were found to be different at different span locations. The boundary layer measurement results for both wings were found to be different at the same angles of attack and Reynolds numbers. The flow pattern also showed that the wing’s upper as well as lower surface behaved differently on the same wing under the same measurement conditions. The results showed that the corrugated wing outperformed the conventional wing at low Reynolds number and the stall angle of the corrugated wing was more than the conventional wing.
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Wang, Dou, Qinfeng Lin, Chao Zhou, and Jianghao Wu. "Aerodynamic performance of a self-propelled airfoil with a non-zero angle of attack." Physics of Fluids 34, no. 3 (March 2022): 031901. http://dx.doi.org/10.1063/5.0082283.

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In the natural world, numerous flying creatures generate both thrust and lift by flapping their wings. Aerodynamic mechanisms of forward flight with flapping wings have received much attention from researchers. However, the majority of previous studies have simplified the forward-flight motion of flapping wings to be uniform, and there has been no detailed evaluation of the validity of this simplification. Motivated by this, aerodynamic characteristics of a self-propelled flapping wing with a non-zero angle of attack were investigated. The results showed that the asymmetric leading-edge vortex produced in the wing's upstroke and downstroke leads to transient thrust, driving the self-propelled wing to move with variable forward velocities. Compared to the uniform forward-flight cases, significant losses in lift and severe changes in the flow field were observed in self-propelled flapping wings. In addition, the changes in the aerodynamic performance—including the forward propulsion speed, lift, and power efficiency—of the self-propelled flapping wing with changes in various dimensionless parameters were also investigated. The heaving amplitude was shown to have significant effects on lift and propulsion speed of the self-propelled flapping wing, while the effects of ratio between the airfoil density and fluid density as well as the Reynolds number, were relatively small. In most conditions, when the Strouhal number was in the range 0.2–0.4, the self-propelled flapping wing performed well in terms of both lift generation and propulsive efficiency. These research results suggest that it is necessary to consider the fluctuating forward speed in aerodynamic modeling of propulsive flapping wings.
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MARIN, Florin Bogdan, Daniela Laura BURUIANA, Viorica GHISMAN, and Mihaela MARIN. "Deep neural network modeling for CFD simulation of drone bioinspired morphing wings." INCAS BULLETIN 15, no. 4 (December 2, 2023): 149–57. http://dx.doi.org/10.13111/2066-8201.2023.15.4.12.

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In this paper we present a deep neural network modelling using Computational Fluid Dynamics (CFD) simulations data in order to optimize control of bioinspired morphing wings of a drone. Drones flight needs to consider variation in aerodynamic conditions that cannot all be optimized using a fixed aerodynamic profile. Nature solves this issue as birds are changing continuously the shape of their wings depending of the aerodynamic current requirements. One important issue for fixed wing drone is the landing as it is unable to control and most of the time consequences are some damages at the nose. An optimized shape of the wing at landing will avoid this situation. Another issue is that wings with a maximum surface are sensitive to stronger head winds; while wings with a small surface allowing the drone to fly faster. A wing with a morphing surface could adapt its aerial surface to optimize aerodynamic performance to specific flight situations. A morphing wing needs to be controlled in an optimized manner taking into account current aerodynamics parameters. Predicting optimized positions of the wing needs to consider (CFD) prior simulation parameters. The scenarios for flight require an important number of CFD simulation to address different conditions and geometric shapes. We compare in this paper neural network architecture suitable to predict wing shape according to current conditions. Deep neural network (DNN) is trained using data resulted out of CFD simulations to estimate flight conditions.
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Engels, Thomas, Henja-Niniane Wehmann, and Fritz-Olaf Lehmann. "Three-dimensional wing structure attenuates aerodynamic efficiency in flapping fly wings." Journal of The Royal Society Interface 17, no. 164 (March 2020): 20190804. http://dx.doi.org/10.1098/rsif.2019.0804.

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The aerial performance of flying insects ultimately depends on how flapping wings interact with the surrounding air. It has previously been suggested that the wing's three-dimensional camber and corrugation help to stiffen the wing against aerodynamic and inertial loading during flapping motion. Their contribution to aerodynamic force production, however, is under debate. Here, we investigated the potential benefit of three-dimensional wing shape in three different-sized species of flies using models of micro-computed tomography-scanned natural wings and models in which we removed either the wing's camber, corrugation, or both properties. Forces and aerodynamic power requirements during root flapping were derived from three-dimensional computational fluid dynamics modelling. Our data show that three-dimensional camber has no benefit for lift production and attenuates Rankine–Froude flight efficiency by up to approximately 12% compared to a flat wing. Moreover, we did not find evidence for lift-enhancing trapped vortices in corrugation valleys at Reynolds numbers between 137 and 1623. We found, however, that in all tested insect species, aerodynamic pressure distribution during flapping is closely aligned to the wing's venation pattern. Altogether, our study strongly supports the assumption that the wing's three-dimensional structure provides mechanical support against external forces rather than improving lift or saving energetic costs associated with active wing flapping.
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Salcedo, Mary K., and John J. Socha. "Circulation in Insect Wings." Integrative and Comparative Biology 60, no. 5 (September 1, 2020): 1208–20. http://dx.doi.org/10.1093/icb/icaa124.

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Synopsis Insect wings are living, flexible structures composed of tubular veins and thin wing membrane. Wing veins can contain hemolymph (insect blood), tracheae, and nerves. Continuous flow of hemolymph within insect wings ensures that sensory hairs, structural elements such as resilin, and other living tissue within the wings remain functional. While it is well known that hemolymph circulates through insect wings, the extent of wing circulation (e.g., whether flow is present in every vein, and whether it is confined to the veins alone) is not well understood, especially for wings with complex wing venation. Over the last 100 years, scientists have developed experimental methods including microscopy, fluorescence, and thermography to observe flow in the wings. Recognizing and evaluating the importance of hemolymph movement in insect wings is critical in evaluating how the wings function both as flight appendages, as active sensors, and as thermoregulatory organs. In this review, we discuss the history of circulation in wings, past and present experimental techniques for measuring hemolymph, and broad implications for the field of hemodynamics in insect wings.
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Mazharmanesh, Soudeh, Jace Stallard, Albert Medina, Alex Fisher, Noriyasu Ando, Fang-Bao Tian, John Young, and Sridhar Ravi. "Effects of uniform vertical inflow perturbations on the performance of flapping wings." Royal Society Open Science 8, no. 6 (June 2021): 210471. http://dx.doi.org/10.1098/rsos.210471.

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Flapping wings have attracted significant interest for use in miniature unmanned flying vehicles. Although numerous studies have investigated the performance of flapping wings under quiescent conditions, effects of freestream disturbances on their performance remain under-explored. In this study, we experimentally investigated the effects of uniform vertical inflows on flapping wings using a Reynolds-scaled apparatus operating in water at Reynolds number ≈ 3600. The overall lift and drag produced by a flapping wing were measured by varying the magnitude of inflow perturbation from J Vert = −1 (downward inflow) to J Vert = 1 (upward inflow), where J Vert is the ratio of the inflow velocity to the wing's velocity. The interaction between flapping wing and downward-oriented inflows resulted in a steady linear reduction in mean lift and drag coefficients, C ¯ L and C ¯ D , with increasing inflow magnitude. While a steady linear increase in C ¯ L and C ¯ D was noted for upward-oriented inflows between 0 < J Vert < 0.3 and J Vert > 0.7, a significant unsteady wing–wake interaction occurred when 0.3 ≤ J Vert < 0.7, which caused large variations in instantaneous forces over the wing and led to a reduction in mean performance. These findings highlight asymmetrical effects of vertically oriented perturbations on the performance of flapping wings and pave the way for development of suitable control strategies.
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Dissertations / Theses on the topic "Wings"

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Liu, Si-Pei [Verfasser], Rolf G. [Gutachter] Beutel, Thomas [Gutachter] Hörnschemeyer, and Alexey [Gutachter] Solodovnikov. "Four wings, two wings, no wings : patterns of wing reduction in Holometabola (Insecta) / Si-Pei Liu ; Gutachter: Rolf G. Beutel, Thomas Hörnschemeyer, Alexey Solodovnikov." Jena : Friedrich-Schiller-Universität Jena, 2019. http://d-nb.info/1179805135/34.

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Biswas, Anindita. "Unwrapping the wings of the television show The West Wing /." Winston-Salem, NC : Wake Forest University, 2008. http://dspace.zsr.wfu.edu/jspui/handle/10339/37493.

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Thesis (M.A.)--Wake Forest University. Dept. of Communication, 2008.
Title from electronic thesis title page. Thesis advisor: Mary M. Dalton. Vita. Includes bibliographical references (p. 102-108).
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Allen, Sheri L. "From the wings." [Gainesville, Fla.] : University of Florida, 2005. http://purl.fcla.edu/fcla/etd/UFE0013367.

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Karlsson, Lotta. "Construction of inflected wings." Thesis, Mälardalens högskola, Akademin för innovation, design och teknik, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-26095.

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Cory, Rick E. (Rick Efren). "Perching with fixed wings." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/43045.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Electrical Engineering and Computer Science, 2008.
Includes bibliographical references (leaves 43-46).
Human pilots have the extraordinary ability to remotely maneuver small Unmanned Aerial Vehicles (UAVs) far outside the flight envelope of conventional autopilots. Given the tremendous thrust-to-weight ratio available on these small machines [1, 2], linear control approaches have recently produced impressive demonstrations that come close to matching this agility for a certain class of aerobatic maneuvers where the rotor or propeller forces dominate the dynamics of the aircraft [3, 4, 5]. However, as our flying machines scale down to smaller sizes (e.g. Micro Aerial Vehicles) operating at low Reynold's numbers, viscous forces dominate propeller thrust [6, 7, 8], causing classical control (and design) techniques to fail. These new technologies will require a different approach to control, where the control system will need to reason about the long term and time dependent effects of the unsteady fluid dynamics on the response of the vehicle. Perching is representative of a large class of control problems for aerobatics that requires and agile and robust control system with the capability of planning well into the future. Our experimental paradigm along with the simplicity of the problem structure has allowed us to study the problem at the most fundamental level. This thesis presents methods and results for identifying an aerodynamic model of a small glider at very high angles-of-attack using tools from supervised machine learning and system identification. Our model then serves as a benchmark platform for studying control of perching using an optimal control framework, namely reinforcement learning. Our results indicate that a compact parameterization of the control is sufficient to successfully execute the task in simulation.
by Rick E. Cory.
S.M.
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Wood, Alice. "Of wings and wheels." Thesis, University of Edinburgh, 2007. http://hdl.handle.net/1842/2022.

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What are the biblical cherubim? In the Hebrew Bible, the physical appearance and cultic role of the cherubim are never explicitly elucidated. Largely, the authors assume their audience is familiar with the form and function of these heavenly beings. Yet the portrayal of the cherubim varies from text to text and, sometimes, we are given conflicting information. Previous studies of the cherubim have placed too great an emphasis on archaeological and etymological data. This thesis presents a new synthetic study which prioritises the evidence supplied by the biblical texts. Biblical exegesis, using literary and historical-critical methods, forms the large part of the investigation (chapter 2). The findings arising from the exegetical discussion provide the basis upon which comparison with etymological and archaeological data is made (chapters 3 and 4). It is argued that, with the exception of the book of Ezekiel, the biblical texts are quite consistent in their portrayal of the cherubim. Cherubim are intimately connected with the manifestation of Yahweh and have an apotropaic function in relation to sacred space. They are envisaged with one face and one set of wings. Ps 18:11 = 2 Sam 22:11 suggests that they are quadrupedal. The traditions in the final form of Ezekiel 1-11 mark a shift in the conception of the biblical cherubim. Physically, the cherubim are transmogrified and become enigmatic beasts with four faces and four wings. Their function also changes. Depicted elsewhere as menacing guardians, in Ezekiel they become agents of praise. The results suggest that traditions envisaging the cherubim as tutelary winged quadrupeds were supplanted by traditions that conceived of them as more enigmatic, obeisant beings. In the portrayal of the cherubim in Ezekiel and Chronicles, we can detect signs of a conceptual shift that prefigures the description of the cherubim in post-biblical texts, such as The Songs of the Sabbath Sacrifice and the Enochic texts.
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Yun, Seunghyun. "Wings-2 for orchestra." College Park, Md. : University of Maryland, 2004. http://hdl.handle.net/1903/178.

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Thesis (D.M.A.) -- University of Maryland, College Park, 2004.
Thesis research directed by: School of Music. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.
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Georghiades, George A. "Aeroelastic behaviour of composite wings." Thesis, City University London, 1997. http://openaccess.city.ac.uk/8054/.

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This research work presents a series of investigations into the structural, dynamic and aeroelastic behaviour of composite wings. The study begins with a literature review where the development of aeroelastic tailoring and specific applications of the technology are discussed in detail. A critique of methods for the determination of cross-sectional rigidity properties follows for beams constructed of laminated and thin-walled materials. Chordwise stiffness is shown to be an important parameter that must be considered as it has a significant effect on the amount of bending-torsion coupling present in a beam and, as a consequence, on the value of torsional rigidity. The free vibration characteristics of such beams are then examined using the dynamic stiffness matrix method. Natural frequencies and mode shapes of various beams are studied using the fibre angle, β, and the bending-torsion coupling which is measured (in this study) by the non-dimensional parameter ψ, as design variables. The results show that ψ has only a marginal effect on the natural frequencies of composite beams (wings) but can significantly modify the mode shapes of such beams. It can be used to decouple modes which are geometrically (inertially) coupled in the same way as mass balancing but without a weight penalty. It can also be used to abate the unfavourable coupling introduced by sweep angle. Classical flutter and divergence of swept and unswept uniform cantilever wings are investigated using laminated flat beams (plates) and thin-walled beams of rectangular and biconvex cross-sections. Various parameters, such as, the fibre angle, β, the coupling parameter, ψ, the angle of sweep, Λ, the static unbalance, Xα, and the non-dimensional ratio of the fundamental (uncoupled) bending to fundamental torsional frequency, ωh/ωα, are varied and their subsequent effects on aeroelastic stability are investigated. The importance of torsional rigidity GJ on the flutter of composite wings is shown to be substantial in contrast with ψ, which is generally the most important parameter to be considered when the objective is that of increasing the divergence speed. Modal interchanges in the free vibration and flutter of laminated composite wings are shown to be primarily responsible for behaviour not experienced with metallic wings, in particular the effect of wash-in and wash-out on flutter. The most intriguing features of these investigations, however, are those which show that models adequate for the analysis of composite wings may be based on two parameters, the frequency ratio ωh/ωα and the coupling parameter ψ. Some results are confirmed by independent optimisation studies. Finally, a preliminary investigation is carried out into the flutter suppression and gust alleviation of a laminated composite wing by the use of active controls. The results show that by using an active control in an optimum trailing edge position the gust response of a wing can be significantly alleviated without compromising the already optimised flutter speed by the use of aeroelastic tailoring.
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Lillico, Mark. "Aeroelastic optimisation of composite wings." Thesis, University of Bath, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.362287.

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McClain, A. "Aerodynamics of nonslender delta wings." Thesis, University of Bath, 2004. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.401655.

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Books on the topic "Wings"

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Ken, Campbell. -'S wings, -'s wings. [London?: K. Campbell, 1999.

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Pratchett, Terry. Wings. New York: HarperTrophy, 2004.

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Pratchett, Terry. Wings. New York: Delacorte Books, 1991.

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Danielle, Steel. Wings. London: Transworld, 2009.

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Pike, Aprilynne. Wings. Waterville, Me: Thorndike Press, 2010.

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Stratton-Porter, Gene. Wings. Princess Anne, MD: Yestermorrow, Inc., 1987.

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Maria. Wings. USA: PublishAmerica, 2004.

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Lethcoe, Jason. Wings. New York: Penguin USA, Inc., 2009.

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Leake, Diyan. Wings. Chicago, IL: Heinemann Library, 2007.

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Pike, Aprilynne. Wings. New York: HarperCollins, 2009.

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Book chapters on the topic "Wings"

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Vogel, Harold L. "Wings." In Travel Industry Economics, 47–117. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27475-1_2.

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Filipovitch, Anthony, Samiul Hasan, Damien Rousseliere, Klodjan Seferaj, Sabine Campe, Damien Rousseliere, Harry Bauer, et al. "WINGS." In International Encyclopedia of Civil Society, 1644–45. New York, NY: Springer US, 2010. http://dx.doi.org/10.1007/978-0-387-93996-4_480.

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Pato, Michele T. "Wings." In Nerve, 89–92. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-33433-7_15.

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Cope, David. "Mottled Wings." In On the Bridge, 84. Totowa, NJ: Humana Press, 1986. http://dx.doi.org/10.1007/978-1-4612-4830-9_78.

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Megson, T. H. G. "Wings." In Aircraft Structures for Engineering Students, 653–86. Elsevier, 2013. http://dx.doi.org/10.1016/b978-0-08-096905-3.00039-5.

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Megson, T. H. G. "Wings." In Introduction to Aircraft Structural Analysis, 639–72. Elsevier, 2018. http://dx.doi.org/10.1016/b978-0-08-102076-0.00022-1.

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Megson, T. H. G. "Wings." In Aircraft Structures for Engineering Students, 663–96. Elsevier, 2017. http://dx.doi.org/10.1016/b978-0-08-100914-7.00023-2.

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Megson, T. H. G. "Wings." In Introduction to Aircraft Structural Analysis, 587–618. Elsevier, 2010. http://dx.doi.org/10.1016/b978-1-85617-932-4.00022-1.

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Nolan, Cathal J. "Wings." In Mercy, C13–261. Oxford University PressNew York, 2022. http://dx.doi.org/10.1093/oso/9780190077280.003.0014.

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Abstract War in the air hardly seems to allow for mercy as fighting reduces to machine versus machine, today using fire-and-forget missiles that streak miles beyond human control. Similarly with bombing. Compared to infantry aiming a rifle, it is much harder to engage empathy for ant-like figures below who scurry over an orangish target grid. It is much closer to long-range artillery, which also kills out of sight and direct moral awareness. This chapter points to rough moral and psychological equations that lower empathy as distance or as altitude and distance increase from bomber to target. It discusses how air war presents in popular media an almost antiseptic violence wherein machines only kill other machines, and the ground explosions are so massive that they obliterate all obscenity. Yet, it also provides examples of moral exceptions from the two world wars that show even in air war, acts of mercy are still possible. It closes with consideration of the moral implications of using drones in targeted killings, and the moral harm inflicted on operators.
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"Wings." In Travel Industry Economics, 35–74. Cambridge University Press, 2001. http://dx.doi.org/10.1017/cbo9781139167130.003.

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Conference papers on the topic "Wings"

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Bou-Mosleh, Charbel, and Samir Patel. "CFD-Based Aerodynamic Analysis of Damaged Delta Wings." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-38420.

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This paper addresses the aerodynamic response of damaged delta wings using steady-state Computational Fluid Dynamics simulations. Two types of delta wings are investigated: a High Speed Civil Transport (HSCT) wing and a F16 Block 40 Wing. These types of analyses are required to help predict wings’ remaining flight capability, after damage is inflicted (during battle). The damage is represented by a hole in the CFD model of both wings. Variations in the shape, size, location and orientation of holes are investigated. The lift and drag (at relatively low angles of attack) of the undamaged and damaged wings are predicted and compared. The obtained numerical results indicate that the location of the hole has a significant effect on the performance of the wing. Furthermore, straight-edged holes seem to have a larger impact on the wing’s aerodynamics as opposed to cylindrical-shaped holes. To make the shape of the hole as realistic as possible, petals emerging above the surface of the wing are introduced and their effect is also investigated. Results show a greater increase in drag compared to smooth cylindrical holes. Finally, and to better simulate the jet in cross flow mainly the strong-jet phenomenon, preliminary time-accurate high angles of attack simulation results will be presented.
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Jankauski, Mark A. "Passive Pitch Mechanics of Elastic Flapping Wings." In ASME 2018 Dynamic Systems and Control Conference. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/dscc2018-8942.

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Many flapping wing micro air vehicles (FWMAVs) utilize a flexible joint that allows the wing to passively rotate about the pitching axis. Generally, simple rigid body models are used to estimate the passive pitching dynamics. However, evidence suggests elastic wings increase aerodynamic force generation and expend less energy relative to rigid wings. As a result, elastic wings are becoming an integral part of FWMAV design. But, the effect of wing elasticity on passive pitching mechanics is unclear. To explore this, we develop a coupled model of an elastic wing attached to a flexible pitching joint. Aerodynamic moments are included through a simple blade element approach. The model is applied to an idealized insect forewing subject to prescribed roll rotation. The simulation results suggest (1) aerodynamic moments, not rigid body inertia or elastic forces, are primarily responsible for lift-generating passive pitch, (2) joint stiffness influences pitching mechanics more than wing elasticity does, and (3) flexible wings can increase net lift by as much as 20% if the pitching joint is mistuned. The framework developed in this paper can be used to design and optimize FWMAV systems in terms of both elastic wings and flexible passive pitch joints.
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Marino, Luca. "A Simple Model Revisited for Wing-Wings and Wings Ground Interference Problems." In 21st AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-4063.

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Otaka, Saimon, Aatsushi Tate, and Takashi Yoshinaga. "Wing rock of double delta wings." In AIAA Atmospheric Flight Mechanics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-4078.

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Roberts, Luke, Hugh A. Bruck, and Satyandra K. Gupta. "Autonomous Loitering Control for a Flapping Wing Miniature Aerial Vehicle With Independent Wing Control." In ASME 2014 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/detc2014-34752.

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Flapping wing miniature aerial vehicles (FWMAVs) offer advantages over traditional fixed wing or quadrotor MAV platforms because they are more maneuverable than fixed wing aircraft and are more energy efficient than quadrotors, while being quieter than both. Currently, autonomy in FWMAVs has only been implemented in flapping vehicles without independent wing control, limiting their level of control. We have developed Robo Raven IV, a FWMAV platform with independently controllable wings and an actuated tail controlled by an onboard autopilot system. In this paper, we present the details of Robo Raven IV platform along with a control algorithm that uses a GPS, gyroscope, compass, and custom PID controller to autonomously loiter about a predefined point. We show through simulation that this system has the ability to loiter in a 50 meter radius around a predefined location through the manipulation of the wings and tail. A simulation of the algorithm using characterized GPS and tail response error via a PID controller is also developed. Flight testing of Robo Raven IV demonstrated the success of this platform, even in winds of up to 10 mph.
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Jacob, J. D. "On the Fluid Dynamics of Adaptive Airfoils." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-0950.

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Abstract This paper discusses issues and practical requirements for an adaptive wing in relation to currently available technology. Adaptive wings offer many benefits, but a viable wing will require research into several areas, including selection of initial and perturbed airfoil shapes, steady and unsteady aerodynamic analysis of adaptive airfoils, and methods for real-time shape control of an adaptive wing system. An overview of adaptive wing history is briefly covered, including some recent developments. Development considerations for an adaptive wing system are then discussed. Aerodynamic performance and stability should be considered in the context of the wing’s structural integrity and aeroelasticity. Particular attention should be paid to the unsteady nature of the flow, as standard quasi-steady flow analysis techniques should be abandoned due to the rapid changes in wing shape and motion. Due to the large number of variable and measured parameters, an advanced control system is required to relate the flight conditions with changes in geometry. Issues related to adapting wings to various aircraft scales will be discussed, specifically micro aerial vehicles (μAVs). unmanned aerial vehicles (UAVs or RPVs), full-scale aircraft, and ornithopters.
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Healy, Richard, and Farhan Gandhi. "Wing Lift Enhancement from Aft Rotor Induced Suction." In Vertical Flight Society 78th Annual Forum & Technology Display. The Vertical Flight Society, 2022. http://dx.doi.org/10.4050/f-0078-2022-17478.

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This study examines the aerodynamic interactions of rotor-wing units in which lifting rotors are mounted below and behind a wing. The rotor-wing units are simulated using CFD, and their performance is compared to isolated rotors and wings in order to understand the interference effects. Simulations are performed using the commercial Navier Stokes solver, AcuSolve®, with a delayed detached eddy simulation (DDES) model. Rotor-wing units with three wing incidence angles (7°, 10° and 13°) as well as three rotor disk loadings (6, 9 and 12 lb/ft2) are considered. By simulating the flow and comparing the pressure distribution around an isolated wing to one with the rotor installed, the rotor is seen to introduce a low pressure region that extends over the wing’s top surface. The additional rotor-induced suction on the top surface of the wing augments wing lift by up to 134%, and provides some stall mitigation at 13° incidence angle. Suction near the leading edge of rotor-installed wings also counters the nominal wing drag, introducing a net propulsive force on the wing at all incidence angles considered. On the rotor, downwash induced by the wing’s bound circulation introduces a rotor thrust deficit up to 10% nominal thrust and torque penalty up to 4% nominal torque. Despite the rotor performance penalties, interactions between the rotor and wing lead to equivalent lift to drag ratio improvements ranging from 47%- 52% over a range of wing angles. As disk loading is increased, the rotor-induced suction strengthens, extending the 66% wing lift increment at 6lb/ft2 up to 115% at 12 lb/ft2. These results suggest that the interactional aerodynamics associated with mounting a rotor below and behind a wing can introduce enhanced system performance over a range of wing angles and rotor loadings.
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Gerdes, John W., Luke Roberts, Eli Barnett, Johannes Kempny, Ariel Perez-Rosado, Hugh A. Bruck, and Satyandra K. Gupta. "Wing Performance Characterization for Flapping Wing Air Vehicles." In ASME 2013 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/detc2013-12479.

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Flapping wing air vehicles offer many useful flight characteristics due to their versatility, as proven by flying animals. Wing design significantly influences the performance. However designing successful wings presents significant challenges. Efficient matching of the drive motors to the flapping wings is necessary to overcome the highly constrained weight budget. Simulating detailed information about the force response due to flapping is challenging due to complex fluid-structural interactions of the wings resulting in non-linear force response to flapping motion. To overcome this challenge, we conducted an experimental study of flapping wings to provide detailed temporal force response data for flapping wings. A prototype was built by synthesizing lightweight manufacturing techniques with the results of the experimental study. Our experimental investigations enabled us to select the flapping angle range and flapping frequency.
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Haluzová, Kristína, Martin Bugaj, and Michal Hrúz. "Aircraft airfoils." In Práce a štúdie. University of Žilina, 2023. http://dx.doi.org/10.26552/pas.z.2023.1.01.

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This work deals with the airfoils of aircraft. First of all, it focuses on the general properties of wings. Furthermore, the work deals with the issue of various types of wing shape and compares individual shapes of airfoils, their properties and gradual development. Next, current wings of commercial aircraft are described, dealing with the materials used, types of winglets, mechanization of the wing and also different uses of the airfoils. The work also describes and compares wings of two famous commercial airliners – Boeing 737-800 and Airbus A320-200. In the end, the work also focuses on various concepts of the wings of the future, and how sustainability affects future development.
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Zhang, Xiaoqin, and Ling Tian. "Numerical Simulation of Micro Air Vehicles With Membrane Wings." In 2007 First International Conference on Integration and Commercialization of Micro and Nanosystems. ASMEDC, 2007. http://dx.doi.org/10.1115/mnc2007-21265.

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Micro Air Vehicles (MAVs) have advantages of small size, low cost, flexibility and controllability etc., so they will be applied widely in military and civilian fields. They have obviously low Reynolds number aerodynamics, which is different from traditional aircrafts. In this paper, numerical simulation based on fluid-structure interaction for flexible wing MAVs is presented. Flexible wings are composed of carbon frames and covered with membrane skins. Because flexible wing MAVs easily deform in airflow, both structure model and fluid model should be built. The two models are connected by interfaces of membrane wings, which transmit distributed pressure and deformations of membrane wings. When membrane wings are located in airflow, they will deform with actions of surrounding airflow. Deformation of membrane wings also affects airflow and pressure distributed on the wings’ surfaces will also be changed relatively, which will compel the shape of membrane wings to be changed once more. Therefore, numerical simulation of flexible wing MAVs is not only the analysis of fluid field, but also the structure deformation effects. Navier-Stokes Equations are nonlinear and complicated, so direct interaction of fluid and structure equations is rather difficult and costs too much time. Indirect interaction method is more feasible and it is adopted in this paper. Structure deformation and distributed pressure on membrane wings surfaces are calculated separately, and then pressure distribution from fluid solver is transmitted to structure solver. After structure deformation is calculated in structure solver, it will be transmitted to fluid field again. Iteration goes on in this way and finally converges. Simulation results show the deformation, stress and pressure distribution of flexible wings. All these results are good reference for MAVs design, modification and wind tunnel experiments generally.
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Reports on the topic "Wings"

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Rade, Domingos A., and Francisco J. de Souza. Variable Camber Morphing Wings. Fort Belvoir, VA: Defense Technical Information Center, February 2016. http://dx.doi.org/10.21236/ad1009258.

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Garcia-Luna-Aceves, J. J., Chane L. Fullmer, Ewerton Madruga, David Beyer, and Thane Frivold. Wireless Internet Gateways (WINGS). Fort Belvoir, VA: Defense Technical Information Center, January 1997. http://dx.doi.org/10.21236/ada461596.

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Jensen, Harry. To Clip an Osprey's Wings. Fort Belvoir, VA: Defense Technical Information Center, December 1991. http://dx.doi.org/10.21236/ada440796.

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Egge, William L. Logistics Implications of Composite Wings. Fort Belvoir, VA: Defense Technical Information Center, December 1993. http://dx.doi.org/10.21236/ada275381.

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Khan, Zaeem A., and Sunil K. Agrawal. Wing Force & Moment Characterization of Flapping Wings for Micro Air Vehicle Application. Fort Belvoir, VA: Defense Technical Information Center, February 2005. http://dx.doi.org/10.21236/ada433708.

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Dailey, Ashlee R., and Karen A. McCall. Summary Report: WINGS 2014 Interoperability Drill. Office of Scientific and Technical Information (OSTI), January 2015. http://dx.doi.org/10.2172/1242499.

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Russell, Horace, and Reginald G. Williams. Cross Flow Over Double Delta Wings. Fort Belvoir, VA: Defense Technical Information Center, February 1994. http://dx.doi.org/10.21236/ada363041.

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Telionis, Demetri. Post Stall Control of Swept Wings,. Fort Belvoir, VA: Defense Technical Information Center, January 1995. http://dx.doi.org/10.21236/ada299820.

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Mahanty, Sango. Asia’s poultry industry spreads its wings. East Asia Forum, August 2023. http://dx.doi.org/10.59425/eabc.1692871228.

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Telionis, Demetri. Post Stall Flow Control Over Swept Wings. Fort Belvoir, VA: Defense Technical Information Center, July 2001. http://dx.doi.org/10.21236/ada398139.

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