Relevant bibliographies by topics / Winglets

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
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Academic literature on the topic 'Winglets'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Winglets"

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Pratiwi, Henny. "THE EFFECTS OF ANGLE OF ATTACK, REYNOLD NUMBERS AND WINGLET STRUCTURE ON THE PERFORMANCE OF CESSNA 172 SKYHAWK." Angkasa: Jurnal Ilmiah Bidang Teknologi 10, no. 1 (May 23, 2018): 61. http://dx.doi.org/10.28989/angkasa.v10i1.206.

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This research aims to investigate the effects of angle of attack, Reynold numbers and winglet structure on the performance of Cessna 172 Skyhawk aircraft with winglets variation design. Winglets improve efficiency by diffusing the shed wingtip vortex, which reducing the drag due to lift and improving the wing’s lift over drag ratio. In this research, the specimens are the duplicated of Cesnna 172 Skyhawk wing with 1:40 ratio made of balsa wood. There are three different winglet designs that are compared with the one without winglet. The experiments are conducted in an open wind tunnel to measure the lift and drag force with Reynold numbers of 25,000 and 33,000. It can be concluded that the wings with winglets have higher lift coefficient than wing without winglet for both Reynold numbers. It was also found that all wings with winglets have higher lift-to-drag ratio than wings without winglet where the blended 45o cant angle has the highest value.
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de Mattos, Bento Silva, Paulo Jiniche Komatsu, and Jesuíno Takachi Tomita. "Optimal wingtip device design for transport airplane." Aircraft Engineering and Aerospace Technology 90, no. 5 (July 2, 2018): 743–63. http://dx.doi.org/10.1108/aeat-07-2015-0183.

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Purpose The present work aims to analyze the feasibility of wingtip device incorporation into transport airplane configurations considering many aspects such as performance, cost and environmental impact. A design framework encompassing optimization for wing-body configurations with and without winglets is described and application examples are presented and discussed. Design/methodology/approach modeFrontier, an object-oriented optimization design framework, was used to perform optimization tasks of configurations with wingtip devices. A full potential code with viscous effects correction was used to calculate the aerodynamic characteristics of the fuselage–wing–winglet configuration. MATLAB® was also used to perform some computations and was easily integrated into the modeFrontier frameworks. CFD analyses of transport airplanes configurations were also performed with Fluent and CFD++ codes. Findings Winglet provides considerable aerodynamic benefits regarding similar wings without winglets. Drag coefficient reduction in the order of 15 drag counts was achieved in the cruise condition. Winglet also provides a small boost in the clean-wing maximum lift coefficient. In addition, less fuel burn means fewer emissions and contributes toward preserving the environment. Practical implications More efficient transport airplanes, presenting considerable lower fuel burn. Social implications Among other contributions, wingtip devices reduce fuel burn, engine emissions and contribute to a longer engine lifespan, reducing direct operating costs. This way, they are in tune with a greener world. Originality/value The paper provides valuable wind-tunnel data of several winglet configurations, an impact of the incorporation of winglets on airplane design diagram and a direct comparison of two optimizations, one performed with winglets in the configuration and the other without winglets. These simulations showed that their Pareto fronts are clearly apart from each other, with the one from the configuration with winglets placed well above the other without winglets. The present simulations indicate that there are always aerodynamic benefits present regardless the skeptical statements of some engineers. that a well-designed wing does not need any winglet.
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Shyu, Jin-Cherng, and Jhao-Siang Jheng. "Heat Transfer Enhancement of Plate-Fin Heat Sinks with Different Types of Winglet Vortex Generators." Energies 13, no. 19 (October 7, 2020): 5219. http://dx.doi.org/10.3390/en13195219.

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Because the delta winglet in common-flow-down configuration has been recognized as an excellent type of vortex generators (VGs), this study aims to experimentally and numerically investigate the thermo-hydraulic performance of four different forms of winglet VGs featuring sweptback delta winglets in the channel flow in the range 200 < Re < 1000. Both Nusselt number and friction factor of plate-fin heat sinks having different forms of winglets, including delta winglet pair (DWP), rectangular winglet pair (RWP), swept delta winglet pair (SDWP), and swept trapezoid winglet pair (STWP), were measured in a standard wind tunnel without bypass in this study. Four rows of winglets with in-line arrangement were punched on each 10-mm-long, 0.2-mm-thick copper plate, and a total of 16 pieces of copper plates with spacing of 2 mm were fastened together to achieve the heat sink. The projected area, longitudinal and winglet tip spacing, height and angle of attack of those winglets were fixed. Besides that, three-dimensional numerical simulation was also performed in order to investigate the temperature and fluid flow over the plate-fin. The results showed that the longitudinal, common-flow-down vortices generated by the VGs augmented the heat transfer and pressure drop of the heat sink. At airflow velocity of 5 m/s, the heat transfer coefficient and pressure drop of plain plate-fin heat sink were 50.8 W/m2·K and 18 Pa, respectively, while the heat transfer coefficient and the pressure drop of heat sink having SDWP were 70.4 W/m2·K and 36 Pa, respectively. It was found that SDWP produced the highest thermal enhancement factor (TEF) of 1.28 at Re = 1000, followed by both RWP and STWP of similar TEF in the range 200 < Re < 1000. The TEF of DWP was the lowest and it was rapidly increased with the increase of airflow velocity.
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Guerrero, Joel, Marco Sanguineti, and Kevin Wittkowski. "CFD Study of the Impact of Variable Cant Angle Winglets on Total Drag Reduction." Aerospace 5, no. 4 (December 3, 2018): 126. http://dx.doi.org/10.3390/aerospace5040126.

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Winglets are commonly used drag-reduction and fuel-saving technologies in today’s aviation. The primary purpose of the winglets is to reduce the lift-induced drag, therefore improving fuel efficiency and aircraft performance. Traditional winglets are designed as fixed devices attached at the tips of the wings. However, because they are fixed surfaces, they give their best lift-induced drag reduction at a single design point. In this work, we propose the use of variable cant angle winglets which could potentially allow aircraft to get the best all-around performance (in terms of lift-induced drag reduction), at different angle-of-attack values. By using computational fluid dynamics, we study the influence of the winglet cant angle and sweep angle in the performance of a benchmark wing at a Mach number of 0.8395. The results obtained demonstrate that by carefully adjusting the cant angle, the aerodynamic performance can be improved at different angles of attack.
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Guerrero, J. E., M. Sanguineti, and K. Wittkowski. "Variable cant angle winglets for improvement of aircraft flight performance." Meccanica 55, no. 10 (September 9, 2020): 1917–47. http://dx.doi.org/10.1007/s11012-020-01230-1.

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Abstract Traditional winglets are designed as fixed devices attached at the tips of the wings. The primary purpose of the winglets is to reduce the lift-induced drag, therefore improving aircraft performance and fuel efficiency. However, because winglets are fixed surfaces, they cannot be used to control lift-induced drag reductions or to obtain the largest lift-induced drag reductions at different flight conditions (take-off, climb, cruise, loitering, descent, approach, landing, and so on). In this work, we propose the use of variable cant angle winglets which could potentially allow aircraft to get the best all-around performance (in terms of lift-induced drag reduction), at different flight phases. By using computational fluid dynamics, we study the influence of the winglet cant angle and sweep angle on the performance of a benchmark wing at Mach numbers of 0.3 and 0.8395. The results obtained demonstrate that by adjusting the cant angle, the aerodynamic performance can be improved at different flight conditions.
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Yang, Yang, Siddharth Koushik Mohanakrishnan, David S.-K. Ting, and Steve Ray. "DELTA WINGLETS FOR ENHANCING SOLAR ENERGY: TURBULENT STRAIN RATE-HEAT CONVECTION RELATIONSHIP." Journal of Green Building 16, no. 2 (March 1, 2021): 97–114. http://dx.doi.org/10.3992/jgb.16.2.97.

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ABSTRACT Delta winglets are an effective means for enhancing heat exchange and thus the performance of renewable energy technologies, including solar energy. A pair of 0.1 mm thick, 15 mm high (h) and 30 mm long aluminum winglets separated with transversal spacing, s, of 2h, h and 0 were scrutinized in a closed-loop wind tunnel at a Reynolds number based on h of 6300. The turbulent flow was characterized using a 3D hotwire probe, and the heat convection augmentation was quantified in terms of the normalized Nusselt number (Nu/Nu0), indicating the heat transfer improvement compared to the reference case without the winglets. The interaction of the organized counter-rotational vortices intensifies and they become indiscernible at s = 0. The peak strain rate at 10h downstream increased from 390 s–1, to 478 s–1, to 514 s–1, when the spacing decreased from 2h to h to 0, respectively. The zero-spaced winglet pair provided the largest Nu/Nu0, of around 1.21, at X/h = 10 and Y/h = 0, approximately 21% higher than that of 2h-spaced winglet pair, due to the strongest strain rate and the absence of upwash flow. On the other hand, the 2h-spaced winglet pair provided the largest span-averaged Nu/Nu0, which is of practical significance.
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Suwannapan, Supattarachai, Panuwat Hoonpong, Pongjet Promvonge, Sirisawat Juengjaroennirachon, and Monsak Pimsarn. "Experimental Study on Flow Friction and Heat Transfer in a Square-Duct Heat Exchanger with Winglet Turbulators." Advanced Materials Research 931-932 (May 2014): 1183–87. http://dx.doi.org/10.4028/www.scientific.net/amr.931-932.1183.

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The paper presents an experimental study on airflow friction and heat transfer behaviors in a heat exchanger square-duct fitted with winglet turbulators. The experiments are carried out by varying the airflow rate in terms of Reynolds number from 4000 to 25,000. The winglets were mounted in tandem with three attack angles (α=30o, 45o and 60o), two winglet-pitch to duct-height ratios, (called pitch ratio, PR=P/H=1.0 and 1.5) and a single winglet-to duct-height ratio, (called blockage ratio, BR=e/H=0.2). Effects of the winglet parameters on heat transfer and pressure loss in terms of Nusselt number and friction factor are investigated. The experimental result reveals that the application of the winglets provides considerably higher heat transfer and pressure loss values than the smooth duct alone. The winglet at α=60o and PR=1 gives the maximum heat transfer and pressure loss but the one at α = 30o and PR=1.5 yields the highest thermal enhancement factor of about 1.49 at the lowest Reynolds number.
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Wu, Wanyang, and Jingjun Zhong. "Experimental investigation of the influence on compressor cascade characteristics at high subsonic speed with pressure surface tip winglets." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 235, no. 6 (January 31, 2021): 1257–71. http://dx.doi.org/10.1177/0957650921990198.

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To investigate the influence of tip winglets on the tip leakage flow in a compressor cascade with different incidences, the experimental measurement combined with numerical simulation are used to study the conventional cascade and cascades with three different pressure surface tip winglets at five incidences of −6°, −3°, 0°, +3° and +6°. The results indicate that three different tip winglets at five incidences all restrain the occurrence of leakage flow, delay the mixing of leakage flow and the mainstream, change the formation path of leakage vortex and weaken its intensity, reduce the flow loss and improve the uniformity of flow field. The sensitivity of the flow field to variable incidences is reduced. The optimization degree of the flow field is proportional to the width of the blade tip winglet. The improvements are more obvious at positive angles. When the incidence reaches +6°, the flow loss is reduced by 12.4%.
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Bera, Kamal K., and Naresh K. Chandiramani. "Aeroelastic flutter control of a bridge using rotating mass dampers and winglets." Journal of Vibration and Control 26, no. 23-24 (March 20, 2020): 2185–92. http://dx.doi.org/10.1177/1077546320915341.

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Flutter control of a bridge deck section using a combination of aerodynamic and mechanical measures, that is controllable winglets and rotating mass dampers, is considered. Deck and winglets are considered as flat plates for their aerodynamics. Self-excited wind forces are represented in the time domain using the Scanlan–Tomko model with Roger’s rational function approximation for flutter derivatives. Winglet rotation relative to the deck is the control input generated by the variable-gain output feedback controller that uses vertical and torsional displacements of the deck as measured outputs. Control using winglets enhances the critical speed to twice the uncontrolled flutter speed. Further attenuation of vertical response is obtained by using rotating mass dampers configured to provide only a resultant vertical force due to counter-rotating unbalanced masses. The rotors are driven at a constant angular speed, and start–stop criteria are applied. This generates additional vertical force on the deck that is mostly out of phase with its vertical velocity. It yields better control than the damper operated in a continuous rotation mode for a fixed number of cycles. A maximum reduction of 15% in root mean square vertical response is obtained when compared with control using winglets only.
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Семків, Тарас Олегович, and Дмитро Миколайович Зінченко. "Adaptive winglets." MECHANICS OF GYROSCOPIC SYSTEMS, no. 35 (May 15, 2018): 75–81. http://dx.doi.org/10.20535/0203-3771352018143891.

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Dissertations / Theses on the topic "Winglets"

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Duong, Thang. "Analys av potentialen för rörliga winglets på framtidens kortdistansflygplan." Thesis, Mälardalens högskola, Akademin för innovation, design och teknik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-35742.

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Flygindustrin fortsätter kontinuerligt att växa, med nyare och effektivare flygplan skapar flygbolagen en konkurrenskraft flygbolag emellan samtidigt som de säkrar deras egna framtid med vinster och besparingar i respektives ekonomi. Syftet med denna rapport är att bedöma potentialen för rörliga winglets på framtidens kortdistansflygplan. Kan detta koncept skära ner på flygbolagens ekonomi? Med oljeprisets historiska utveckling går det att fastställa att olika händelser runtom i världen kan påverka utveckling antingen negativt eller positivt. Genom konceptet rörliga winglets kan flygbolag förebygga de negativa konsekvenserna av oljeprisutvecklingen och i bästa fall öka de positiva konsekvenserna. För att bedöma potentialen fokuseras arbetet på följande två frågeställningar: Kan anpassningsbara winglets leda till en förbättring? Hur ser de mekaniska- och aerodynamiska krafterna ut på wingletsen vid förbättring?   Angreppsättet av frågeställningarna har gått till på sådant vis att krafterna som verkar på wingletsen har gjorts om till vektorer. Genom att vektorer användes för att undersöka frågeställningarna blev det lättare att illustrera samt matematiskt beräkna effekterna vid olika kantvinklar och anfallsvinklar. Resultatet visade att det finns en förbättringsmöjlighet på dagens winglets. Dock finns det mycket kvar att göra gällande andra aspekter som också berör potentialen.
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Kauertz, Sebastian. "Beeinflussung des Wirbelnachlaufs eines Tragflügels mit aktiven winglets /." Aachen : Shaker, 2006. http://bvbr.bib-bvb.de:8991/F?func=service&doc_library=BVB01&doc_number=016032698&line_number=0001&func_code=DB_RECORDS&service_type=MEDIA.

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Muñoz, Hernán Darío Cerón. "Análise experimental das características aerodinâmicas de multi-winglets adaptativas." Universidade de São Paulo, 2004. http://www.teses.usp.br/teses/disponiveis/18/18135/tde-28102015-155234/.

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O objetivo desta pesquisa é o estudo do uso potencial de multi-winglets adaptativas para obter reduções no arrasto induzido através da variação do diedro das winglets. Os vórtices gerados nas pontas das asas são um produto inevitável da presença da sustentação, ou seja, é um custo a pagar pela força que mantém as aeronaves no ar. Diferentes estudos têm demonstrado que o escoamento presente nas pontas das asas pode ser redirecionado usando pequenas superfícies aerodinâmicas reduzindo assim o arrasto induzido. O modelo testado era constituído por uma asa retangular construída a partir de um perfil NACA 653 - 018 dotado de três winglets tipo \"tip-sails\", que são pequenas asas sem enflechamento ao 25% da corda. Os testes realizados foram para um regime de Número de Reynolds de 357.000. Os resultados foram analisados através da análise da sustentação, arrasto e mapeamento da esteira através da técnica de anemometria de fio quente.
The aim of this research is the study of the potential use of adaptive multi-winglets to reduce induced drag through variations of winglet cant angles. The vortices generated at the wing tips are an inevitable product of the presence of lift, that is, they represent the price paid for the presence for the force that keeps the aircraft in the air. Different studies have shown that the flow over the wing-tip can be redirected using small aerodynamics surfaces, thereby reducing the induced drag. The model tested is composed of a rectangular wing using a NACA 653 - 018 profile with three winglets called \"tip-sails\", which are small wings without sweep at 25% chord. The tests were made at a Reynolds number of 350,000. The results are analyzed in terms of lift and drag and mapping of the wake using hot wire anemometry techniques.
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Rosescu, Justin J. "A Study of the Design of Adaptive Camber Winglets." DigitalCommons@CalPoly, 2020. https://digitalcommons.calpoly.edu/theses/2177.

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A numerical study was conducted to determine the effect of changing the camber of a winglet on the efficiency of a wing in two distinct flight conditions. Camber was altered via a simple plain flap deflection in the winglet, which produced a constant camber change over the winglet span. Hinge points were located at 20%, 50% and 80% of the chord and the trailing edge was deflected between -5° and +5°. Analysis was performed using a combination of three-dimensional vortex lattice method and two-dimensional panel method to obtain aerodynamic forces for the entire wing, based on different winglet camber configurations. This method was validated against high-fidelity steady Reynolds Averaged Navier-Stokes simulations to determine the accuracy of these methods. It was determined that any winglet flap deflections increased induced drag and parasitic drag, thus decreasing efficiency for steady level flight conditions. Positive winglet flap deflection at higher lift conditions may increase efficiency, but the validity of the vortex lattice method results for these conditions are dubious. A high-fidelity method should be used for the high lift condition to obtain accurate efficiency data.
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Broomfield, Susannah Elizabeth. "Large deflection, nonlinear loads analysis, with application to large winglets." Thesis, University of Bristol, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.492476.

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The inclusion of static aeroelastic effects is essential to the accurate calculation of the aerodynamic properties of a wing, the resulting wing loads, and ultimately the mass of the wing. Within an industrial aircraft design cycle, the computational time required for structurally coupled nonlinear flow solvers is impractical for the many different solutions required, even with the current development in computing power. The process currently used by most civilian aircraft manufacturers therefore makes use of time efficient linear panel methods for calculating the aerodynamics and modal data for calculating structural movements.University of Bristol.
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Kauertz, Sebastian [Verfasser]. "Beeinflussung des Wirbelnachlaufs eines Tragflügels mit aktiven Winglets / Sebastian Kauertz." Aachen : Shaker, 2006. http://d-nb.info/1166514803/34.

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Junior, Sergio Luiz Lousada. "Análise comparativa de winglets em uma aeronave regional de última geração." Instituto Tecnológico de Aeronáutica, 2011. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=3023.

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O presente trabalho visa determinar, via análises de dados de túnel de vento, o impacto aerodinâmico em arrasto da instalação de dispositivos de ponta de asa em uma aeronave transônica de transporte moderna, para averiguar o ganho atingido com os atuais métodos de projeto de winglets. São comparados 3 dispositivos de ponta de asa, em uma campanha de ensaios em túnel. Os ensaios foram realizados à pressão total constante, fazendo o uso dos mesmos suportes, e realizando as mesmas variações no escoamento. Os dados colhidos em diversas rodadas de túnel foram então analisados procurando estabelecer qual a influência de cada dispositivo sob o arrasto da aeronave, em regimes subsônicos e transônicos. As comparações puderam estabelecer que o atual estado da arte oferece reduções significativas de arrasto em cruzeiro, proporcionando melhorias no alcance e outras características de desempenho da aeronave, vindo a comprovar a teoria e os dados históricos de desempenho destes dispositivos.
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Rajendran, Saravanan. "Design of Parametric Winglets and Wing tip devices : A Conceptual Design Approach." Thesis, Linköpings universitet, Fluida och mekatroniska system, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-80721.

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Winglets being a small structure play an important role in reducing the induced drag in aircraft. Many types of winglets have been designed and their significance in reducing the drag is published. One of the main objectives of this master thesis work is to study about the winglet design and about their contribution in reducing induced drag. A brief overview of wing tip devices and their performance from the manufacturers as well as from airliner’s point of view are discussed. Moreover, the role of winglet in reducing the drag of commercial civil jet aircraft is studied and the percentage of drag reduction is calculated by a conceptual approach. A320 specifications are taken to perform induced drag reduction calculation with and without winglets. Indeed, the total drag count reduced with the help of winglets accounts for additional payload which will be an advantage for the aircraft operator. Reducing the process time in design is one of the important criteria for any field and hence automation with help of CAD tools is very significant in reducing time. This study also aims at developing an automated model for different types of winglets and wing tip devices with the help of CAD technology focused on reducing design time during the initial design process.  Knowledge based approach is used in this work and all the models are parameterized so each model could be varied with associated parameters. The generic model created would take different shapes and switches between different types of wing tip devices as per the user’s requirement with the help of available parameters. Knowledge Pattern (KP) approach is used to develop the automation process. User Defined Features (UDFs) are created for each type of winglet and tip devices. CATIA V5 R18 software is used to develop the models of winglets and tip devices.
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Lawson, Michael James. "Practical Applications of Delta Winglets in Compact Heat Exchangers with Louvered Fins." Thesis, Virginia Tech, 2006. http://hdl.handle.net/10919/34141.

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Compact heat exchangers are widely used by the automotive industry in systems that cool engine components. Louvered fin heat exchangers are used over their continuous fin counterparts because of the significant advantages they provide in heat transfer efficiency, while only causing small increases in overall pressure losses. With the recent emphasis that has been placed on reducing fuel consumption, decreasing the size of the compact heat exchanger has become an important concern. With reduction in size comes not only weight savings, but also a decrease in frontal area in a vehicle that must be dedicated to the heat exchanger, allowing for more aerodynamic vehicle designs.

Air-side resistance on the tube wall and louvered fin surfaces comprises over 85% of total resistance to heat transfer in louvered fin heat exchangers. The tube wall surface is considered the primary surface for heat transfer, where the temperature between the working fluid and convecting air is at a maximum. Recent studies have shown that implementing delta winglets on louvered fins along the tube wall is an effective method of augmenting tube wall heat transfer. In this thesis, the effect of delta winglets is investigated in both two- and three-dimensional louvered fin arrays. For both geometries, winglets are simulated in a manufacturable configuration, where piercings in the louvered fins that would result from the winglet manufacturing process are modeled.

Using the two-dimensional geometry to model tube wall heat transfer was shown not to accurately predict heat transfer coefficients. In a two-dimensional geometry, winglets were found not to be an effective means for augmenting tube wall heat transfer and caused only 8% augmentation. Using the three-dimensional geometry, winglets with simulated piercings were observed to cause up to 24% tube wall heat transfer augmentation, with a corresponding increase in pressure losses of only 10%.


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Farhan, Ali M. "Numerical study of the effect of winglets on a horizontal axis wind turbine performance." Thesis, University of Leeds, 2018. http://etheses.whiterose.ac.uk/22493/.

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With increasing demand for producing clean and pollution free energy, special attention has been paid to wind turbines and improving their performance. Reducing the effect of wingtip vortices on the wind turbine performance can be achieved by using winglets which work to weaken the impact of wingtip vortices by diffusing them away from the blade tips. The general trend of the literature has considered winglets as diffusers of the wingtip vortices. However, extending the span of the turbine rotor by attaching winglet could improve the potential of a rotor to capture more kinetic energy from moving air. Accordingly, the winglet planform and airfoil play vital roles in wind turbines performance. The present work reports on the study of the effect of winglet planform and winglet airfoil on the wind turbine performance using Computational Fluid Dynamics (CFD) tools. The National Renewable Energy Laboratory (NREL) phase VI rotor is used as a baseline rotor and the CFD results are validated with the experimental data in terms of torque, pressure and normal force coefficients for different wind speeds. In this study, two turbulence models are used, which are the SST k-ω and the Spalart-Allmaras models, which can be used to predict the properties of the fluid flow in the computational domain. Both of the models show a good match of the numerical results when compared to the experimental data, at a range of low wind speeds from 5m/s to 8m/s, due to the absence of stalled flow. At higher wind speeds of 10m/s, the SST k-ω model shows a better match between the calculated torque and the experimental measurements. Consequentially, the SST k-ω model is implemented to predict the behaviour of fluid flow in all the CFD calculations in the present study. The aerodynamic behaviour of two winglet planforms is investigated. These are rectangular and elliptical winglets to increase the NREL phase VI rotor performance. The performances of four winglet configurations are assessed when compared to the baseline power, at the range of wind speeds from 5m/s to 25m/s. The configurations are obtained by changing the winglet planforms and airfoils using the S809 and PSU 94-097 airfoils. In this regard, the elliptical planform causes a minimizing of the wingtip vortices, more than the rectangular planform, due to the reduction of the elliptical tip by 75% when compared to the rectangular tip. A rectangular planform shows a better performance than the elliptical planform in percentages of power increase. The highest percentage in the power increase is achieved by attaching the rectangular planform that tilted by a cant angle of 45o and extended by 15cm. This improvement is slightly more than 9%, at the range of low wind speeds from 5m/s to 10m/s, since the flow is almost attached. Considering the effect of winglet airfoil, the study reports that, choosing a suitable winglet airfoil is mainly dependent on the aerodynamic coefficients of the selected airfoil, such as lift coefficient (Cl), drag coefficient (Cd) and moment coefficient (Cm). For this purpose, a preliminary analysis is conducted using the Xfoil code to predict the aerodynamic coefficients of selected airfoils (S801, S803, S805A and S806A airfoils). The S806A and S805A airfoils are chosen to create two different configurations. The 3D calculations show more increase in the NREL phase VI power is achieved by attaching the configuration that created using the S806A airfoil since this airfoil has less drag coefficient.
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Books on the topic "Winglets"

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Smith, Leigh Ann. Effects of winglets on the drag of a low-aspect-ratio configuration. Hampton, Va: Langley Research Center, 1996.

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Smith, Leigh Ann. Effects of winglets on the drag of a low-aspect-ratio configuration. Washington, DC: National Aeronautics and Space Administration, 1996.

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3

Meyer, Robert R. Effects of winglets on a first-generation jet transport wing: VII - Sideslip effects on winglet loads and selected wing loads at subsonic speeds for a full-scale model. Edwards, Calif: Dryden Flight Research Facility, 1986.

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4

Ruhlin, Charles L. Effects of winglet on transonic flutter characteristics of a cantilevered twin-engine-transport wing model. Hampton, Va: Langley Research Center, 1986.

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Kuhlman, John M. Theoretical/numerical study of feasibility of use of winglets on low aspect ratio wings at subsonic and transonic Mach numbers to reduce drag. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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Cookson, Catherine. The wingless bird. London: Corgi, 1996.

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Cookson, Catherine. The wingless bird. London: Corgi, 1991.

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Cookson, Catherine. The wingless bird. Leicester: Ulverscroft, 1991.

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Cookson, Catherine. The wingless bird. Thorndike, Me: Thorndike Press, 1991.

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Cookson, Catherine. The wingless bird. London: Corgi Books, 1991.

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Book chapters on the topic "Winglets"

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Dhileep, Karthick, S. Arunvinthan, and S. Nadaraja Pillai. "Aerodynamic Characteristics of Semi-spiroid Winglets at Subsonic Speed." In Lecture Notes in Mechanical Engineering, 217–24. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-2718-6_20.

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Chen, Yuwen, and Martin Fiebig. "Effect of Fin Heat Conduction on the Performance of Punched Winglets in Finned Oval Tubes." In Heat Transfer Enhancement of Heat Exchangers, 107–22. Dordrecht: Springer Netherlands, 1999. http://dx.doi.org/10.1007/978-94-015-9159-1_7.

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Sarangi, S. K., and D. P. Mishra. "Thermo-Fluid Performance Evaluation of an Elliptical Tube Type Fin-and-Tube Heat Exchanger Supported with Winglets." In Lecture Notes in Mechanical Engineering, 23–33. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-33-4165-4_3.

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Gratwick, Marion. "Wingless weevils." In Crop Pests in the UK, 210–15. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-1490-5_43.

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Drezga, Danijel, Viken Korian, Olaf Roock, Bernardo Lopez, Arne Fiedler, Stefan Storm, and Vladimir Snop. "Winglet Design, Manufacturing, and Testing." In Smart Intelligent Aircraft Structures (SARISTU), 257–73. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_13.

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Legent, Kevin, and Jessica E. Treisman. "Wingless Signaling in Drosophila Eye Development." In Methods in Molecular Biology, 141–61. Totowa, NJ: Humana Press, 2008. http://dx.doi.org/10.1007/978-1-60327-469-2_12.

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Wildschek, Andreas. "Influence of H 2 and $$ {{\mathcal{L}}}_{\infty } $$ Criteria on Feed-Forward Gust Loads Control Optimized for the Minimization of Wing Box Structural Mass on an Aircraft with Active Winglets." In Smart Intelligent Aircraft Structures (SARISTU), 319–31. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_16.

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Ashcroft, Bill. "Primitive and Wingless: the Colonial Subject as Child." In Dickens and the Children of Empire, 184–202. London: Palgrave Macmillan UK, 2000. http://dx.doi.org/10.1057/9780230294172_14.

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Nusse, R., E. Rulifson, M. Fish, C. Harryman-Samos, M. Brink, C.-h. Wu, and K. Cadigan. "Interactions Between Wingless and Frizzled Molecules in Drosophila." In Of Fish, Fly, Worm, and Man, 1–11. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-04264-9_1.

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Gonsalves, Foster C., and Ramanuj DasGupta. "Function of the Wingless Signaling Pathway in Drosophila." In Methods in Molecular Biology, 115–25. Totowa, NJ: Humana Press, 2008. http://dx.doi.org/10.1007/978-1-60327-469-2_10.

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Conference papers on the topic "Winglets"

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Shivaramaiah, Subbaramu, Quamber H. Nagpurwala, Mahesh K. Varpe, and H. K. Narahari. "Effect of Rotor Tip Winglet on the Performance and Stability of a Transonic Axial Compressor." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4686.

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Winglets are plane surfaces with certain thickness and different shapes. Winglets are used in aircraft to reduce wing tip vortex which is created due to differential pressure in between pressure surface and suction surface. In transonic axial compressor, rotor tip leakage vortex interaction with shock layer and shroud boundary layer leads to total pressure loss and initiation of stall phenomenon. Effect of tip winglets are investigated in compressor rotor cascade. Cascade investigation shows that rotor tip winglet are able to reduce total pressure loss due to tip leakage flow and blade passage secondary flow. Cascade studies are performed with winglet on blade suction side, pressure side and combination of both. From cascade studies it is revealed that suction side winglet are aerodynamically better than pressure side and combined winglets. Owing to favorable results of tip winglet on compressor cascade performance, it was assumed that tip winglets would enhance overall performance of transonic compressor stage with rotating rotor. Results of present CFD simulations have predicted both positive and negative effects of winglets. Effect of different winglet configurations on pressure side and suction side of rotor blade tip are investigated to analyze the compressor stage overall performance. Rotor tip winglets are able to increase stage total pressure ratio compare to the baseline stage without winglet. Stage with winglets have shown better performance in choke region. Winglets are able to vary rotor blade loading from hub to tip region. Presence of winglet has shown ability to reduce to total pressure loss in trailing edge wake region. Stall margin is decreased in compressor stage with winglets due to more blockage towards trailing edge in tip region.
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Guha, Tufan Kumar, William Oates, and Rajan Kumar. "Characterization of Piezoelectric Macrofiber Composite Actuated Winglets." In ASME 2014 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/smasis2014-7598.

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Piezoelectric macro-fiber composite (MFC) structures have been used to develop oscillating winglets for active control of wing-tip vortices. A MFC structure was embedded inside a wing-section to oscillate the winglet at its free end. The goal is to weaken the potentially harmful tip vortices by introducing controlled instabilities through both spatial and temporal perturbations produced by an oscillating winglet. In the present study we have characterized MFC actuated winglets under different input excitation and pressure loading conditions. It consisted of bench-top experiments to characterize the structural resonance, with and without point pressure loading and wind tunnel tests involving distributed pressure loading. Surface pressure measurements were carried out at three spanwise locations to measure the effect of oscillating winglet on the pressure distributions on the wing surface. MFC actuated winglets show bimodal resonance behavior and the modes of oscillations are independent of magnitude of input excitation and the pressure loading.
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Hernandez-Rivera, Ricardo, Abel Hernandez-Guerrero, Cuauhtemoc Rubio-Arana, and Raul Lesso-Arroyo. "Numerical Study in Wing Tip Vortex for a Modified Commercial Boeing Aircraft." In ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-68149.

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Recent studies have shown that the use of winglets in aircrafts wing tips have been able to reduce fuel consumption by reducing the lift-induced drag caused by wing tip vortex. This paper presents a 3-D numerical study to analyze the drag and lift forces, and the behavior of the vortexes generated in the wing tips from a modified commercial Boeing aircraft 767-300/ER. This type of aircraft does not contain winglets to control the wing tip vortex, therefore, the aerodynamic effects were analyzed adding two models of winglets to the wing tip. The first one is the vortex diffuser winglet and the second one is the tip fence winglet. The analyses were made for steady state and compressible flow, for a constant Mach number. The results show that the vortex diffuser winglet gives the best results, reducing the core velocity of the wing tip vortex up to 19%, the total drag force of the aircraft up to 3.6% and it leads to a lift increase of up to 2.4% with respect to the original aircraft without winglets.
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Gupta, Alka, and R. S. Amano. "CFD Analysis of Wind Turbine Blade With Winglets." In ASME 2012 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/detc2012-70679.

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This study is aimed at investigating the aerodynamic performance of the wind turbine blade with winglets and compares its performance in terms of the power generated with a regular straight blade without winglet. Adding a winglet to the wind turbine blade improves the power production without increasing the projected rotor area. A parameter study is carried out where two of the key parameters which describe a winglet design namely the cant angle and the winglet height are varied. The winglet is bent towards the pressure (upstream) side. Pro/ENGINEER is used to generate a straight wind turbine blade which is then modified in SPACECLAIM to attach a winglet to it. Single blade analysis approach is chosen to carry out the computation, as this involves less computational time and low cost. Results show that adding a winglet to a straight blade increases its power output by 2% to 20%. In addition, winglet which has a cant angle of 45° performs better, generating more power than the winglet which is perpendicular to the blade (cant angle 90°). Also, the power generation increases with the increase in the winglet height. Amongst the four winglet designs discussed, the design W4 with cant angle of 45° and winglet height of 4% rotor radius performs the best resulting in 20% improvement in the power generation when added to a straight blade.
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Demasi, Luciano, Giovanni Monegato, Rauno Cavallaro, and Rachel Rybarczyk. "Minimum Induced Drag Conditions for Winglets: the Best Winglet Design Concept." In AIAA Scitech 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-2301.

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Bera, K. K., and N. K. Chandiramani. "Flutter Suppression of Bridge Deck Section Using Controllable Winglets Driven by LQR Control." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-70847.

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Active flutter control of bridge deck section using controllable winglets is studied. Self-excited wind forces acting on deck and winglets are modeled using the Scanlan-Tomko model. Vertical, lateral and torsional degrees of freedom are considered for deck and corresponding eighteen experimental flutter derivatives (FD) are used. Winglets are modeled as flat plates and FDs are obtained from Theodorsen functions. Time domain formulation using Rogers rational function approximation leads to divergence speed much lower than the actual one, which is confirmed by Quasi steady theory. Hence, for control study, the usual trial and error method involving sweeping through speed and frequency is used. Rotations of winglets relative to deck are considered as control input, rather than the driving torque. Full state feedback with LQR control is applied. The state variables are estimated by designing a full order observer system using pole placement technique. Winglet rotations being restricted within bounds, the flutter behavior is studied using closed loop responses and compared with eigenvalue analysis. Numerical results shows the implemented control strategy is quite effective in flutter suppression and enhancing the flutter speed.
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Coull, John D., Nicholas R. Atkins, and Howard P. Hodson. "High Efficiency Cavity Winglets for High Pressure Turbines." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25261.

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The flow leaking over the tip of a high pressure turbine blade generates significant aerodynamic losses as it mixes with the freestream flow. This paper examines the potential for reducing these losses using winglets with recessed cavities on the tip. These features combine the loss-reduction mechanisms of cavity tips, which reduce the discharge coefficient, and winglet overhangs, which reduce the mixing Mach number, leakage flow angle mismatch, and the driving pressure ratio. RANS calculations are performed for an un-cooled HP rotor blade to explore the cavity-winglet design space and examine the impact on the aerothermal performance of the blade. Relative to a plain-tip design, a cavity tip can reduce the sensitivity to clearance by around 30%. Similar performance can be achieved using a flat-tip winglet with an overhang around the whole blade perimeter. However, by adding a cavity to this winglet it is possible to out-perform the cavity tip at all clearances, and reduce the sensitivity to clearance by 46% relative to the plain tip. This sensitivity is equivalent to a two-fin attached shroud, but the winglet blade will exhibit lower stress and require less coolant flow. Furthermore this cavity-winglet may offer some cooling advantages over the cavity tip.
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Wu, Wanyang, Jingjun Zhong, Xiaoxu Kan, and Zhenyu Huang. "Influence of Pressure Surface Winglets on the Tip Leakage Flow in a Compressor Cascade With High Subsonic Mach Numbers." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14218.

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Abstract The improvement of compressor performance is facing a new technological challenge, as the compressor is considered as one of the core components in a gas turbine. Tip leakage flow affects the aerodynamic performance of the compressor rotor directly, then the compressor performance can be improved by reasonably controlling it. In recent years, the blade tip winglet has been certainly concerned as an effective flow control method for reducing the leakage loss. The mechanism of using tip winglets to control tip leakage flow in compressor cascade has been investigated in the condition of low Mach number, whereas the research in high subsonic incoming conditions also needs to be considered. To investigate the effect of the pressure surface winglet on the aerodynamic performance of a compressor cascade at high subsonic inlet Mach numbers, an experiment compared cascades with no winglet and different width pressure surface tip winglets at different inlet Mach numbers (Ma = 0.5, 0.6 and 0.7). Results show that the pressure surface winglet weakened the pressure gradient on both sides of the blade and reduced flow loss in the condition of high subsonic Mach numbers, which in turn tip clearance flow. When pressure surface tip winglet width increased, the improving degree is increased. At the same time, a change in Mach number had a proportional the effect on tip leakage flow control. The most effective pressure surface winglet was PW2.0 at the inlet Mach number of 0.7, which produced the most significant cascade loss reduction of 6.53% when compared to the original cascade at the same inlet Mach number. To investigate the characteristics of the compressor cascade at different incidences, the Mach number was set at 0.7 and the characteristics of cascade flow at −6°, −3°, 0°, +3° and +6°were studied. Pressure surface winglets with different widths reduced both the influence range of the leakage flow and the strength of the leakage vortex. As the tip winglet width increased, the influence of the tip winglet on the cascade flow increased. When incidences moved from negative to positive, the improvement effect of the cascade flow field with the pressure surface winglet was enhanced. When the incidence was+6°, for example the improvement effects the PW2.0 on cascade loss was 12.4%. The flow characteristics in the compressor cascade with the pressure surface winglets behave better at different Mach numbers and incidences. Through the research in this paper, the improvement effect and mechanism of the aerodynamic performance of the pressure surface winglet in high subsonic Mach number are clearer, and the application range of the winglet is widened, which provides a rich reference for the optimization design of compressor with high subsonic Mach number.
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Miklosovic, D. S., and P. M. Bookey. "An Analytic and Experimental Investigation of the Aerodynamic Performance Enhancements of Multiple Winglet Configurations." In ASME 2005 Fluids Engineering Division Summer Meeting. ASMEDC, 2005. http://dx.doi.org/10.1115/fedsm2005-77255.

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An experimental effort was undertaken to assess the effectiveness and efficiency of three winglets mounted chordwise to the tip of a rectangular wing (NACA 0018 section). The winglets, with an aspect ratio of 3.6, were mounted on a half-span wing having an aspect ratio of 3.1. Twenty configurations of varying dihedral arrangements were analyzed with a vortex lattice method and tested in a low-speed wind tunnel at a Reynolds number of 600,000. In general, the arrangements involving high dihedral angles had lower performance increments, due to lower lift and higher interference drag. More specifically, the results showed that the winglets placed at 60, 45, and 30 degrees, respectively, produced nominal 4% higher lift and 46% lower drag. The most dramatic findings from this study show that positioning the winglet dihedral angles had the result of adjusting the point of maximum L/D and the magnitude of the pitching moment coefficient. These observations suggest that multiple winglet dihedral changes affect the lift, drag, and pitching moment in such a way that they are feasible for use as actively-controlled surfaces to improve the performance of aircraft at various flight conditions and to “tune” the longitudinal stability characteristics of the wing.
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Fonte, Federico, Giuseppe Iannaccone, Nicola Cimminiello, Ignazio Dimino, and Sergio Ricci. "Active Load Control of a Regional Aircraft Wing Equipped With Morphing Winglets." In ASME 2018 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/smasis2018-8167.

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Morphing winglets are innovative aircraft devices capable to adaptively enhance aircraft lift distribution throughout the flight mission while providing augmented roll and yaw control capability. Within the scope of the Clean Sky 2 REG IADP, this paper deals with nonlinear simulations of a regional aircraft wing equipped with active morphing winglets in manoeuvring conditions. The fault tolerant morphing winglet architecture is based on two independent and asynchronous control surfaces with variable camber and differential settings capability. The mechanical system is designed to face different flight static and dynamic situations by a proper action on the movable control tabs. The potential for reducing wing and winglet loads by means of the winglet control surfaces is numerically assessed by means of static aeroelastic analyses, using a feedforward manoeuvre load alleviation controller. An electro-mechanical Matlab/Simulink model of the actuation architecture is used as design tool to preliminary evaluate the complete system performance and the ability to cope with the expected morphing aeroshapes. Then, the aeroelastic model of the aircraft is combined with the nonlinear simulator of the response of the winglet actuation system to evaluate a symmetric and asymmetric manoeuvres obtained by a sudden deflection of the main control surfaces. The use of the morphing winglet tabs shows to alleviate the wing loads in such conditions. The introduction of the dynamic actuator model leads to a reduction of the performances with respect to predictions of the static analyses but a reduction of the manoeuvre loads can still be observed.
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Reports on the topic "Winglets"

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Smith, M. J., N. Komerath, R. Ames, O. Wong, and J. Pearson. Performance Analysis of a Wing With Multiple Winglets. Fort Belvoir, VA: Defense Technical Information Center, January 2001. http://dx.doi.org/10.21236/ada454384.

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Cumberledge, Susan. Biochemistry and Molecular Mechanisms of Wingless Action. Fort Belvoir, VA: Defense Technical Information Center, September 1995. http://dx.doi.org/10.21236/ada305797.

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Nusse, Roel. Isolation of a Receptor for WNT/Wingless Growth Factors. Fort Belvoir, VA: Defense Technical Information Center, September 1996. http://dx.doi.org/10.21236/ada319774.

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Nusse, Roel. Isolation of a Receptor for WNT/Wingless Growth Factors. Fort Belvoir, VA: Defense Technical Information Center, September 1995. http://dx.doi.org/10.21236/ada301701.

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Nusse, Roel. Isolation of a Receptor for WNT/Wingless Growth Factors. Fort Belvoir, VA: Defense Technical Information Center, September 1998. http://dx.doi.org/10.21236/ada366728.

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Nusse, Roel. Isolation of a Receptor for WNT/Wingless Growth Factors. Fort Belvoir, VA: Defense Technical Information Center, September 1999. http://dx.doi.org/10.21236/ada382531.

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