Wing Elements Research Articles

Design and CFD Analysis of a Rear Wing of a Motorsport Car

The rear wing of a motorsport car is one of the 3 main components to produce the downforce required by the car to take a corner with the maximum speed possible. This paper aims to design and analyse the rear wing of a motorsport car. The design consists of a lower wing element (main plane), an upper wing element (flap) and the endplates. In this study, the rear wing is designed as per the FIA 2020 F1 technical regulations and is analyzed using Computational Fluid Dynamics (CFD). The rear wing model is designed using Autodesk Fusion 360 and the analysis is made using Autodesk CFD. Benzing airfoils were used in this project as the wing elements. The results of the stock and modified model are compared and discussed. The results show how the modified version of the endplate has better aerodynamic properties than the stock model. The whole rear wing assembly has also been analysed and the results were discussed.

Geometric morphometric analysis of the humerus in New and Old World vultures.

The vulture guild is composed of two distinct groups, Old and New World, which provide a unique insight into how morphology varies among convergent species. All vultures are considered to be large birds of prey that utilize a style of flight called thermal soaring to search and feed primarily on carrion. Even though this flight style is exhibited among all 23 species, slight variations in their skeletal morphology may relate to their differences in ecology. We hypothesized that vulture humeral morphology varies in relation to these organisms' habitat, average body mass, courtship displays, and migratory behavior. To address this hypothesis, we used three-dimensional geometric morphometrics to measure the overall shape differences of vulture humeri. Humeral morphology was found to vary most by habitat association and migratory tendency. The humeri of vultures that inhabit forested areas exhibit features that suggest increased flapping flight compared to those in open and mountainous regions. Migratory species were found to possess more robust features near the glenohumeral joint. We found these (and other features) have some utility for predicting ecology and behavior, but we suggest that further investigation into skeletal and muscular wing elements may reveal greater understanding of the habits of extinct vulture species.

The osteology of Ferrodraco lentoni, an anhanguerid pterosaur from the mid-Cretaceous of Australia

ABSTRACT Ferrodraco lentoni, an anhanguerid from the Upper Cretaceous Winton Formation of northeast Australia, is the most complete Australian pterosaur described to date, represented by a partial cranium, incomplete cervical series and wing elements. Herein we present a comprehensive osteological description of Ferrodraco, as well as an emended diagnosis for this taxon. In addition, we compare Ferrodraco with other isolated pterosaur remains from Australian Cretaceous deposits. Subtle, yet salient, differences indicate that at least three of these specimens, all derived from the upper Albian Toolebuc Formation, are distinct from Ferrodraco. However, we are uncertain whether these specimens are attributable to Mythunga camara, Aussiedraco molnari, Thapunngaka shawi, or an as yet un-named taxon. Detailed description of the postcranial material of Ferrodraco also provides an opportunity to reassess its phylogenetic position. In one analysis, Ferrodraco and Mythunga are resolved as sister taxa within Tropeognathinae, whereas in another, Ferrodraco, Mythunga, and Tropeognathus form a polytomy within Coloborhynchinae. Either way, these slight differences notwithstanding, a close relationship between Ferrodraco and Mythunga is evident, supporting the interpretation that they form a clade. By contrast, Aussiedraco molnari is resolved as a member of Targaryendraconia, a clade with a cosmopolitan distribution. The presence of several anhanguerian taxa or lineages in the late Early and early Late Cretaceous of northeast Australia is suggestive of even greater diversity in the Australian pterosaur fauna.

Buckling-driven mechanisms for twisting control in adaptive composite wings

This study aims to design novel tailorable and effective mechanisms by controlling buckling behaviour in structural elements of a composite wing for future morphing application. Instead of the traditional design against buckling, the idea is to embrace this built-in instability by using the nonlinear post-buckling response to control stiffness changes which redistribute the load in the wing structure. To enable desired multi-stable configurations, three buckling-driven mechanisms are investigated by restraining the out-of-plane buckling deformation using point, area and maximum displacement constraints. Numerical studies of the proposed mechanisms are at first conducted on a composite plate and are later integrated to control twisting of a simplified thin-walled composite wing box. The proposed mechanisms offer effective design opportunities of multi-stable configurations and demonstrate the potential to realise morphing of composite wings employing controlled buckling behaviours in structural components.

Comments on the Morphology of Basal Paravian Shoulder Girdle: New Data Based on Unenlagiid Theropods and Paleognath Birds

In 1976 John Ostrom published an enlightening paper about the anatomical transformations in the shoulder girdle and forelimb elements along the origin of birds. Most of his ideas were based on comparingArchaeopteryx lithographicawith the extant New World vultureCathartes aura. Ostrom offered innovative ideas about range of movements and function of wing elements in the basal birdArchaeopteryx. Further, he explored anatomical transformations that may have occurred at early stages of the evolution of flight and established several hypothetical steps toward the acquisition of flapping flight in modern birds. Since then, however, our understanding of paravian diversity and anatomy has increased dramatically. Based on novel information derived from recent experiments, and currently available anatomical evidence of basal paravians, the present paper aims to review some important topics on pectoral girdle anatomy related to flight origins. Further, a brief analysis of pectoral girdle osteology and myology of the extant paleognathRhea americanais also included with the aim to test whether Ostrom’s ideas still remain valid under this new context, based on available phylogenetic and anatomical frameworks.

Neolithic avifaunal resource utilisation in the lower Yangtze River: A case study of the Tianluoshan site

The lower Yangtze River region in China was a centre of early Neolithic rice cultivation and animal domestication. It is also an important habitat for wintering birds; however, our current understanding of prehistoric avifaunal resource utilisation by human populations in this region is limited. To clarify the use of birds by early Neolithic rice-cultivating societies further, we analysed bird remains from one excavation grid at the Tianluoshan site, which dates to between 7000 and 6100 cal BP. Ducks (Anatinae), rails (Rallidae), and geese (Anserinae) were dominant in every layer, suggesting that birds wintering in inland waters were the primary avifaunal taxa exploited at the Tianluoshan site. The taxonomic composition, bone modification rate, and skeletal part representation of these dominant taxa differed between layers. Overall, there was an abundance of duck and goose wing elements and both the wing and leg elements of rails, suggesting that exploitation patterns differed among these primary taxa. There is no evidence of domestic exploitation of ducks and/or chickens (Gallus gallus domesticus), but the appearance of immature goose bones may suggest the existence of domestic geese.

АНАЛІЗ СИЛ ФУНКЦІОНУВАННЯ ВІД’ЄМНОЇ ЧАСТИНИ КРИЛА ЛІТАКА ТРАНСПОРТНОЇ КАТЕГОРІЇ

Each experimental design department has experience in determining design and operational loads for a given type of aircraft. The reliability of the data on the loading of a particular structural element determines the success of the aircraft being created. This is often confidential information. Much work has been investigated to improve the fatigue life of wing structural elements. With the development of integrated design methods, aircraft structure design can be performed in the shortest time, and with high technical excellence. In most cases, the fatigue life of wing elements is determined from the nominal stresses in the element. For a longitudinal structure set, it is customary to perform fatigue calculations directly using normal stresses in the element. For a more detailed specification of the fatigue life, it is necessary to have a general and local stress-strain state of a given structure. A feature of the work is to analyze the spectrum of loads acting on the wing console during a typical flight. The influence of high-lift devises (slats, flaps) on the shear forces and torque moment of the wing was analyzed. It has been shown that with the extensions high-lift devices, there is a significant increase in torque. These articles will make it possible to obtain the stress distribution of the detachable part of the wing under all operating modes. This, in turn, leads to a more thorough prediction of fatigue life. Since some operating loads can significantly change the distribution of the stress-strain state in the design element, and in turn change the fatigue life. The structural elements of the wing, in particular the attachment points for the high-lift devices, operate in a complex-stressed state. This complicates the process of predicting the fatigue life of these elements. To obtain a competitive aircraft, it is necessary to develop new methods of wing design with widespread use of integrated systems. This will contribute to obtaining a more optimal and perfect wing design

Parametric Optimization of Load Bearing Elements for Composite Wing of an Unmanned Aerial Vehicle

This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pareto set method of the “ideal center” basing on four criteria: minimum mass, deflection, normal stress, and maximum safety factor of the wing. Verification calculations were carried out to determine the safety factor of the load-bearing wing structure using a geometrically nonlinear model in FEMAP software.

Natural Vibrations of a Spacecraft’s Solar Array Wing

In the process of deploying the wings of solar arrays of a spacecraft, natural transverse vibrations arise in them. The study of these vibrations is an urgent problem, since in some cases they are capable of disrupting the commutation of photoelectric converters. The transverse vibrations of the wing originate from the connection of its sections when locking (coupling) hinge devices. In this case, the kinetic energy of the sections is converted into the potential energy of natural vibrations of the solar array wing. This problem is traditionally solved by using a finite element model with subsequent calculations in the ANSYS program. The purpose of this study is to develop an approximate analytical method for mathematical modeling of the natural elastic vibrations of elements of the solar array wing arising in the process of its deploying.

Design and Development of Multi Element Wing for Automobile Application

Vehicle aerodynamics is a broad encompassing field that describes the forces acting on an object when moving through a fluid. When stationary, the exterior surfaces of an automobile experience one atmospheric pressure; the upper and lower surface as well as the front and rear surfaces all have the same pressures exerted and ultimately achieve equilibrium with the summation of forces being equal to zero. As the vehicle starts to move through the fluid, the pressures exerted on the exterior surfaces change proportional to the square of velocity. These pressure changes create forces acting on the surface of the vehicle that can drastically hinder the performance of the vehicle. Aerodynamicists study this natural phenomenon to try and minimize forces that inhibit motion and, in some cases, develop these forces and use them to improve performance and safety. Vehicle aerodynamicists are primarily concerned with two dominant forces that interact with a vehicle; lift and drag. The management of these forces is crucial to the performance of any vehicle however the philosophy of vehicle aerodynamics differ significantly depending on the application. In this work introducing multi element in the rear of the vehicle to maintain the lift force and computational fluid dynamics analysis carry out to measure the performance of the multielement wing.

An articulated pterosaur wing from the Upper Cretaceous (Maastrichtian) phosphates of Morocco

A new and articulated specimen of a pterosaur wing including the humerus, radius/ulna, parts of the carpus and metacarpus and a first wing phalanx from Maastrichtian phosphatic deposits of Morocco is assigned to Tethydraco regalis Longrich et al., 2018. Aspect of the humerus morphology, shape of the deltopectoral crest and ratios of the wing elements suggest that T. regalis is an azhdarchid rather than pteranodontian pterosaur, as originally proposed. A high abundance of azhdarchid remains in the open marine setting of the Moroccan phosphates casts doubt on suggestions that Azhdarchidae are largely terrestrial pterosaurs.

A harvestman with elaborate palpal pliers, Thunbergia gretae n. gen. n. sp. from China (Opiliones: Sclerosomatidae: Gagrellinae)

Based on the unusual characteristics of the male pedipalp and male genital morphology, a new genus and new species of Gagrellinae harvestmen, Thunbergia gretae n. gen. n. sp. (male and female) from Shaanxi Province, China, is proposed. The tibia and tarsus of the pedipalp form elaborate palpal claws, resembling gaspipe pliers, probably used to grasp the legs or the pedipalps of the female during courtship. There is no comparable modification of the pedipalp in the female. The penis lacks wing or sac-like (saccate) elements normally present in Gagrellinae, and the penis base is markedly inflated to form a bulb-like structure harbouring the penis muscle. Two or three opisthosomal tergites are fused to the opisthosomal scute and, in combination, cause the male and female bodies to appear elongated and slender. Three further species belong to Thunbergia n. gen., namely Thunbergia grandis (Roewer 1912), Thunbergia wangi (Zhu & Song 1999) and Thunbergia zhui (Zhang & Zhang 2013). The genus Melanopa Thorell, 1889, to which the new species T. gretae n. sp. superficially seems to belong, is re-defined by revision of the type species from Burma (now Myanmar). With respect to courtship behaviour morphological interdependence of penial and of pedipalpal structures within Gagrellinae and Leiobuninae are addressed.

Numerical Investigation of the Unsteady Flow Past an Iced Multi-Element Airfoil

Unsteady flow characteristics are investigated using wall-modeled large-eddy simulation for a 30P30N three-element airfoil with streamwise ice and horn ice accreted at its slat leading edge, respectively. The ice accretions cause massive flow separation above the slat, which results in a surface pressure plateau on the slat and further unloads the downstream wing elements. The above mentioned two ice shapes lead to lift decreases of 10.66 and 16.45% and drag increases of 44.58 and 59.42%, respectively. Ice-induced vortices first roll up due to Kelvin–Helmholtz instability above the slat with ice accretions, and the subsequent vortex pairing halves their characteristic motion frequency. The developed vortices, composed of multiscale structures, dominate the slat upper surface and are convected through the main element to aggravate the flow separation over the flap. Moreover, extremely strong acoustic resonance occurs in the iced slat cove, and its tonal frequencies are consistent with theoretical model predictions. These intense tones are believed to result from the elevated pressure fluctuations along the cavity free shear layer, which are in turn related to the propagation of the ice-induced pressure fluctuations from above the slat because their most dominant frequencies identified by proper orthogonal decomposition are nearly equal to the resonant frequencies.

Experience in the formation of power elements of an aircraft wing using topological optimization approaches

The process of designing aircraft structures, in most cases, involves finding solutions that will minimize weight, while maintaining the characteristics of strength and rigidity. To increase the mass efficiency of the aircraft glider, it is proposed to carry out topological optimization of structural and power elements at the initial stages of design with the help of modern software packages.
 Modern wings of traditional forms are close to exhausting their aerodynamic and weight characteristics, so all over the world there is an intensive search for new technical solutions. This indicates the relevance of developing new methods that use high-precision mathematical modeling in the early stages of design.
 Despite the significant number of publications on the topic of mass optimization, including aircraft structures, there are no quantitative indicators of the magnitude of the possible minimization of mass by topological optimization methods for the main structural and power elements of the aircraft wing.
 The article describes the results of the analysis of the effectiveness of the use of topological optimization methods to minimize the mass of the main structural and power elements of the aircraft wing. For a typical, typesetting structural and power scheme of a light aircraft wing, the values of possible minimization of the glider mass were determined.
 The use of topological optimization at the design stage of the power elements of the aircraft glider makes it possible to significantly reduce the mass of the main structural and power elements and allows to significantly reduce the takeoff mass of the aircraft. This approach using the results of optimization can be used to determine rational power schemes and predict the mass of the wings, taking into account the peculiarities of their geometric shapes and boundary conditions.

An early Oligocene stem Galbulae (jacamars and puffbirds) from southern France, and the position of the Paleogene family Sylphornithidae

AbstractTogether, puffbirds (Bucconidae) and jacamars (Galbulidae) form the suborder Galbulae, sister group of all other Piciformes. Hitherto, the Galbulae had no ascertained pre-Pleistocene fossil record, and all previous alleged candidates have been refuted, except possibly the Sylphornithidae. Here we describe a wing of a tiny fossil bird from the early Oligocene of the Luberon region (southern France), which we assign to the Galbulae, as a new genus and species. Several characters, especially of the ulna and wing phalanx 1 of digit II, exclude the Passeriformes and Zygodactylidae, and indicate a representative of the Piciformes. Among Piciformes, absence of papillae remigales caudales and several characters of the wing phalanx 1 of digit II make it possible to assign the fossil to the Galbulae, and exclude all other clades. The fossil Sylphornithidae, with the carpometacarpus of Sylphornis being available, show some similarity with the Luberon fossil. The combination of features of the wing elements leads to the placement of the new fossil as stem Galbulae, and tentatively within the family Sylphornithidae. As such, it fills a gap and permits to better assign the whole enigmatic tiny sylphornithids, otherwise essentially known from leg bones. This yields the first firm pre-Pleistocene fossil record for the Galbulae. Today, both the Bucconidae and Galbulidae live exclusively in tropical America. The presence of stem Galbulae in the Oligocene of Europe, and probably the late Eocene, is a new example of a present-day Neotropical clade that had stem representatives in the Paleogene of Europe.

Глобально-локальное моделирование односрезных болтовых соединений типа композит — металл и композит — композит в конструктивных силовых элементах самолета

In performing design strength analysis of connection areas of composite — metal and composite — composite types of structural load-bearing wing and empennage elements of the aircraft implemented using mechanical fasteners, it is necessary to considerthe factors determining the local strength of these areas: the conditions of mechanical contact of the body, bolt head and cap with connected elements, the connected elements contact with each other and the effects of friction. These factors can be taken into account only by applying the global-local modeling approach for constructing 3D prediction models of composite — metal and composite — composite joint zones of aircraft caisson structural members. To solve this problem, a method is proposed defining the means and tools of modeling, algorithms for constructing a prediction model and performing calculations, as well as procedures for analyzing the results of calculations.

A Study on the Effect of Debris Location on a Double Element Wing in Ground Effect

<div class="section abstract"><div class="htmlview paragraph">Multi-element front wings are essential in numerous motorsport series, such as Formula 1, for the generation of downforce and control of the onset flows to other surfaces and cooling systems. Rubber tyre debris from the soft compounds used in such series can become attached to the wing, reducing downforce, increasing drag and altering the wake characteristics of the wing. This work studies, through force balance and Particle Image Velocimetry (PIV) measurements, the effect a piece of debris has on an inverted double element wing in ground effect. The debris is modelled using a hard-setting putty and is located at different span and chord-wise positions around the wing. The sensitivity to location is studied and the effect on the wake analysed using PIV measurements. The largest effect on downforce was observed when the debris was located on the underside of the wing towards the endplates. The wake was most effected when the debris was located closest to the gap, generating a large fluctuating wake with a significantly different path to the baseline case.</div></div>

Bone chemical composition changes in bird bones from laboratory exposure to saline lake conditions

The abundance of bird bones in archeological contexts of high salt is potentially impacted by salinization, which can affect bone preservation. We exposed wing elements (humeri, ulnae, and radii) of domestic chicken (Gallus gallus domesticus) to laboratory conditions simulating a saline lake substrate with overlaying saltwater for up to 32 weeks. Our analyses based on bone ashing and elemental concentration using ICP-OES are reported. The data provide useful taphonomic information regarding changes in bone mineral content, element concentrations, and element to phosphorus ratios of bird bones exposed to saline environments. Results showed that all exposed wing bones increased significantly in bone mineral content, which indicated that wing bones most likely became stronger. Overall, ionic concentrations of Ca2+, K+, Mg2+, Na+, P5+, Sr2+, and Si4+, except Fe3+, changed significantly among all wing bones with saline exposure. These changes in ion concentration took place in as little as 4 weeks. Element to phosphorus ratios provided insight into potential ionic substitutions between the bone and the saline substrate and solution exposure. The results from our study provide direct evidence that the chemical composition of bird bones deposited along saline lake shorelines quickly become altered.

Fluid-Structure Interation of a Rigid Wing for Minesto Deep Green, a Tidal Energy Device

Fluid structure interaction (FSI) analysis has been performed on the main wing structure of an underwater renewable energy tidal flow device using methods of different fidelity. A lower fidelity method represented the wing as a series of beams (1D line elements) which deflect and rotate under hydrodynamic load. These deflections and rotations were used to update the geometry for the hydrodynamic model where updated forces and moments were calculated using potential flow theory with integral boundary layer (2D panel methods). The higher fidelity method represented the wing using a combination of 3D solid elements for the foam structure inside the wing and 2D shell elements for the carbon fibre wing stiffening beams and fibre glass wing skin. The results of a modal analysis of the wing structure were used in a 3D CFD simulation that coupled the modal equations with the Navier-Stokes equations to compute the deformed shape of the wing under hydrodynamic load. In both cases, the maximum deformations of the wing were quite small (<25mm) compared to the wing size (12m span, 3.3m maximum chord) but the effect on hydrodynamic characteristics was quite different. The low fidelity analysis made the assumption that the wing cross-sectional shape profile did not change, although it could move and rotate. There was no significant change in the predicted hydrodynamic characteristics between the deformed and undeformed wing shapes. The contribution of the foam to the stiffness of the wing was not included in the low fidelity analysis as it was thought to be minor contributor due the much lower Young’s Modulus compared to the carbon fibre and fibre glass of the main wing structure. In contrast, the high fidelity method resulted in about a 15% reduction in lift and 6% in drag forces due to deformation of the wing cross-section profiles rather than bending and twisting of the wing which the low fidelity analysis showed not to be significant. The effect on energy yield of these changes is estimated to be very small.

Engineering Estimation of the Error of Bending of Angle Blanks in a Tool Die

The challenging problem of ensuring the accuracy of sizes in bending followed by elastic springback of angle parts, which form a wide class of aircraft elements, i.e., stringers, stiffening ribs, and lattice wheel and wing elements, is considered. The purpose of this work is to develop a technique for engineering estimation of the angle error in bending an angle blank in a tool die. The proposed technique reflects the physical features of springback in bending in a tool die, is characterized by simplicity, and provides the accuracy of estimating the angular error that is sufficient for engineering practice. This technique can be used to solve a number of practical problems.