Relevant bibliographies by topics / Wing dihedral

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  1. Journal articles
  2. Dissertations / Theses
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  4. Conference papers

Academic literature on the topic 'Wing dihedral'

Author: Grafiati
Published: 4 June 2021
Last updated: 14 February 2022

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Journal articles on the topic "Wing dihedral"

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Traub, L. W., R. Waghela, and K. A. Bordignon. "Characterisation of a highly staggered spanwise cambered biplane." Aeronautical Journal 119, no. 1212 (February 2015): 203–28. http://dx.doi.org/10.1017/s0001924000010344.

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AbstractAn investigation is presented to elucidate the performance of a staggered, spanwise cambered biplane. The spanwise camber yielded wings forming a ‘∧’ or ‘∨’ when viewed streamwise. The configuration is examined in terms of its aerodynamic and stability characteristics. The feasibility of negating the requirement for a conventional empennage is explored. Geometric variation encompassed front and back wing anhedral/dihedral angles yielding 49 combinations. Evaluation of the geometry was accomplished using both wind tunnel testing and numerical simulation. The results indicated that front wing dihedral in conjunction with aft wing anhedral was most beneficial, such that the benefit of wake spacing was maximised. Aerodynamic benefit was indicated compared to a conventional empennage geometry. The greatest disparity in behaviour of the fore and aft wing anhedral/dihedral distribution was in the high lift regime, where the nature of the stall varied. Simulations to establish the viability of the geometry in terms of controllability were also conducted and indicated that the configuration is viable.
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Phillips, W. F. "Analytical Solution for Wing Dihedral Effect." Journal of Aircraft 39, no. 3 (May 2002): 514–16. http://dx.doi.org/10.2514/2.2960.

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Streit, T., and C. Hoffrogge. "DLR transonic inverse design code, extensions and modifications to increase versatility and robustness." Aeronautical Journal 121, no. 1245 (October 11, 2017): 1733–57. http://dx.doi.org/10.1017/aer.2017.101.

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ABSTRACTThe DLR inverse design code computes the wing geometry for a prescribed target pressure distribution. It is based on the numerical solution of the integral inverse transonic small perturbation (TSP) equations. In this work, several extensions and modifications of the inverse design code are described. Results are validated with corresponding redesign test cases. The first modification concerns applications for high transonic Mach numbers or cases with strong shocks. The introduced modifications enable converged design solutions for cases where the original method failed. The second modification is the extension of the code to general non-planar wings. Previously, the design code was restricted to non-planar wing designs with small dihedral or to nacelle design. A third modification concerns aerofoil/wings designed for wind-tunnel design. In order to design a swept wing between two wind-tunnel walls, the solution method was extended to two symmetry planes. The introduced extensions and modifications have increased the robustness and range of applicability of the inverse design code.
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G., Prasad, Ramesh M., and Rajasekar K. "Numerical Investigation on Effect of Multiple Winglets for Wind Turbine Applications." International Journal of Engineering & Technology 7, no. 4.5 (September 22, 2018): 450. http://dx.doi.org/10.14419/ijet.v7i4.5.20204.

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The present article is an effort to examine the potential of multiple winglets to reduce the induced drag of the aerodynamic surface. The advantages of using multiple winglets include reduction of induced drag, increased L/D and improved performance of the Wind turbine. Computational Fluid Dynamics is utilized as to approach the effects of multiple winglets with NACA 24012 airfoil section for untwisted, rectangular wing. The testing of configurations is done at Reynolds number 290,000. FLUENT solver incorporated in ANSYS used for the numerical investigation of the steady flow over the wing. A substantial improvement in lift curve slope occurs with dihedral spread of the winglets. The dihedral spread also distributes the tip vortices.
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Wang, Zhi Gang, and Zhen Ning Zhang. "Modeling and Simulation of Unsteady Aerodynamics on a Morphing Wing." Applied Mechanics and Materials 427-429 (September 2013): 77–80. http://dx.doi.org/10.4028/www.scientific.net/amm.427-429.77.

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Modeling and simulation method of unsteady aerodynamics on morphing wings were investigated. The Unsteady Vortex Lattice Method is employed to model the unsteady aerodynamics of 3-D potential flow field surrounding the wing. An UVLM computer code was then developed and validated for numerical simulation. A morphing wing which changes its dihedral angle with constant angular velocity was investigated by the code, and the lift, induced drag, and pitching moment coefficients time histories were obtained. The results show that the UVLM code is an effective tool for simulations of unsteady aerodynamics on morphing wings.
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NAKAGAWA, Toru, Satoshi KIKUCHI, Shigeki IMAO, and Yasuaki KOZATO. "207 Effect of Dihedral Angle on Wing in Ground Effect." Proceedings of Conference of Tokai Branch 2011.60 (2011): _207–1_—_207–2_. http://dx.doi.org/10.1299/jsmetokai.2011.60._207-1_.

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Bourdin, P., A. Gatto, and M. I. Friswell. "Performing co-ordinated turns with articulated wing-tips as multi-axis control effectors." Aeronautical Journal 114, no. 1151 (January 2010): 35–47. http://dx.doi.org/10.1017/s0001924000003511.

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Abstract This paper investigates a novel method for the control of aircraft. The concept consists of articulated split wing-tips, independently actuated and mounted on a baseline flying wing. The general philosophy behind the concept was that adequate control of a flying wing about its three axes could be obtained through local modifications of the dihedral angle at the wing-tips, thus providing an alternative to conventional control effectors such as elevons and drag rudders. Preliminary computations with a vortex lattice model and subsequent wind tunnel tests and Navier-Stokes computations demonstrate the viability of the concept for co-ordinated turns, with individual and/or combined wing-tip deflections producing multi-axis, coupled control moments. The multi-axis nature of the generated moments tends to over-actuate the flight control system, leading to some redundancy, which could be exploited to optimise secondary objective functions such as drag or bending moment.
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Wang, Caidong, Chen Wang, Yu Ning, Lumin Chen, and Xinjie Wang. "Design and Mechanical Analysis of Bionic Foldable Beetle Wings." Applied Bionics and Biomechanics 2018 (August 9, 2018): 1–10. http://dx.doi.org/10.1155/2018/1308465.

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In order to improve the flight performance of collapsible aircrafts, a novel mechanism of bionic foldable wings of beetle is designed based on the four-plate mechanism theory. The folding and unfolding movements of the bionic foldable wings are driven by motor and torsion hinges. Based on the D-H method, a kinematic model of wings is established to analyze the dihedral angle of adjacent plates. The folding ratio of an area in different plate creasing angles has been derived and calculated. Utilizing the kinematic and static models produced, as well as considering the folding ratio and output motor torque, the optimal physical parameters of folding wings are obtained. Dynamic models of rigid and flexible wings were established using ADAMS, and a motion simulation was performed. The relationship between dihedral angle and torque during the folding process of both rigid and flexible wings was obtained. The results provide a better understanding of the folding mechanism through the formulation of rigid-flexible wing analysis, as well as demonstrating a novel design of insect-mimicking artificial wings for small aerial vehicles.
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Est, Brian E., and H. F. Nelson. "Fin dihedral effects on wing-body carryover for supersonic noncircular missiles." Journal of Spacecraft and Rockets 32, no. 3 (May 1995): 433–39. http://dx.doi.org/10.2514/3.26633.

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Afonso, F., G. Leal, J. Vale, É. Oliveira, F. Lau, and A. Suleman. "The effect of stiffness and geometric parameters on the nonlinear aeroelastic performance of high aspect ratio wings." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 10 (November 25, 2016): 1824–50. http://dx.doi.org/10.1177/0954410016675893.

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The increase in wing aspect ratio is gaining interest among aircraft designers in conventional and joined-wing configurations due to the higher lift-to-drag ratios and longer ranges. However, current transport aircraft have relatively small aspect ratios due their increased structural stiffness. The more flexible the wing is more prone to higher deflections under the same operating condition, which may result in a geometrical nonlinear behavior. This nonlinear effect can lead to the occurrence of aeroelastic instabilities such as flutter sooner than in an equivalent stiffer wing. In this work, the effect of important stiffness (inertia ratio and torsional stiffness) and geometric (sweep and dihedral angles) design parameters on aeroelastic performance of a rectangular high aspect ratio wing model is assessed. The torsional stiffness was observed to present a higher influence on the flutter speed than the inertia ratio. Here, the decrease of the inertia ratio and the increase of the torsional stiffness results in higher flutter and divergence speeds. With respect to the geometric parameters, it was observed that neither the sweep angle nor the dihedral angle variations caused a substantial influence on the flutter speed, which is mainly supported by the resulting smaller variations in torsion and bending stiffness due to the geometric changes.
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Dissertations / Theses on the topic "Wing dihedral"

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Barbosa, Átila Antunes França. "Influência da asa em gaivota nos coeficientes aerodinâmicos de uma aeronave." Universidade de São Paulo, 2015. http://www.teses.usp.br/teses/disponiveis/18/18148/tde-15112015-170422/.

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Desde o início da década de 2010, o aumento do preço do combustível de aviação e a pressão da sociedade para redução da emissão de gases nocivos ao meio ambiente, junto com a necessidade de redução de ruído durante as fases de decolagem e pouso, levaram as companhias aéreas a buscar aeronaves mais eficientes. Para suprir essa demanda, os fabricantes de aviões comerciais solucionaram esse problema através do uso de motores de maior desempenho, que apresentam maior diâmetro que motores de gerações passadas. Desse modo, foi necessário projetar asas com maior diedro na região da raiz, possibilitando a instalação desses novos motores, e diedro menor após a seção do motor, adotando assim a solução de asa em gaivota. O presente trabalho visa analisar o impacto de diferentes tipos de asas em gaivota nos coeficientes aerodinâmicos de uma aeronave de configuração comercial típica. Para tanto, foi realizada uma revisão bibliográfica dos estudos envolvendo asas em gaivota. Numa primeira fase foi feito um estudo analítico das características aerodinâmicas de alguns modelos de aeronaves com asa em gaivota, e em uma segunda fase, foram empregadas ferramentas computacionais para analisar seus comportamentos aerodinâmicos. Posteriormente, em uma terceira fase, esses modelos foram ensaiados no túnel de vento do LAE (Laboratório de Aerodinâmica da EESC/USP), e os resultados das três fases foram comparados.
Since the beginning of the 2010s, the increasing price of aviation fuel and the pressure of society to reduce the emission of harmful gases into the environment, coupled with the need of noise reduction during the takeoff and landing, induce carrier companies to look for more efficient airplanes. To furnish this demand, the airplane manufacturers solved the problem using high performance engines, which present a larger diameter than the engines from previous generations. Thereby, it was necessary to project wing with higher dihedral on the root portion, enabling the installation of these new engines, and a lower dihedral after the engine section, thus adopting a gull wing solution. This research project aims at analyzing the impact of different types of gull wing on the aerodynamic coefficients of a typical commercial configuration airplane. For this purpose, a bibliographic review about the studies related to gull wings was performed. In a first phase, an analytical analysis of the aerodynamic characteristics of some airplane model with gull wings was done, and in a second phase, computational programs was used to study their aerodynamic behavior. Later, in a third phase, these models were tested in the wind tunnel of LAE (Laboratory of Aerodynamics of EESC/USP), and the results from the three phases were compared.
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Gildutis, Paulius. "Sklandytuvo Lak-17 šoninio stabilumo charakteristikų tyrimas skaitiniu metodu." Master's thesis, Lithuanian Academic Libraries Network (LABT), 2009. http://vddb.library.lt/obj/LT-eLABa-0001:E.02~2009~D_20090626_094658-76316.

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Kompiuterinis geometrinis sklandytuvo Lak-17 modelis sugeneruotas programa AVL, kuri skirta orlaivių konfigūracijos ir skrydžio charakteristikų analizei. Imituojant realų skrydį programa suskaičiuotos įvairios šoninio stabilumo charakteristikos. Tirta, kaip šoninio stabilumo savyb÷ms, tokioms kaip krypties nestabilumas, spiralinis nestabilumas, „olandiškas žingsnis“, turi įtakos skersinio V kampo didinimas ar mažinimas, vertikalios uodegos plokštumos ploto keitimas. Pagal gautus rezultatus suformuluotos išvados kiekvienam šoninio nestabilumo atvejui. Darbą sudaro 3 dalys: įvadas, problemos analiz÷, AVL programos apžvalga, tyrimas, išvados, literatūros sąrašas. Darbo apimtis – 92 p. 65 p. teksto be priedų, 82 iliustr., 6 lent. Atskirai pridedami priedai.
Computer-based geometrical model of sailplane Lak-17 was generated with a program AVL (Athena Vortex Lattice), which is designed for analysis of characteristics of flight and rapid analysis of configuration of aircraft. Analysis was done how increasing and decreasing of wing dihedral and exchange of vertical tail area characteristics are influenced on lateral stability like directional divergence, spiral divergence and „dutch roll“. Simulating a real flight with the program various characteristics of stability and control were calculated. According results the conclusion was formulated for every case of lateral unstability. Structure: introduction, problem analysis, AVL overview, research, conclusions, references. Thesis consist of – 92 p. 65 p. text without appendixes, 82 pictures, 6 tables. Appendixes are included.
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Chen, Bo-Jian, and 陳柏堅. "Analysis of the Blade Dihedral Angle on the Power Output Effect of the Wind Turbine." Thesis, 2008. http://ndltd.ncl.edu.tw/handle/56200011635781843311.

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碩士
國立屏東科技大學
機械工程系所
96
This research studies the effects of blade dihedral angle on the power output of a horizontal axis wind turbine. The purpose is to adjust the dihedral angle to reduce the power output of the blades, such that preventing damage the electric generator from over-speed the system. Both the blade element theory and momentum theory are used to develop the 3-dimensional blade shape, and then the Computational Fluid Dynamics (C.F.D.) method is introduced to resolve the flow-field details, and evaluate the performance of the system. The 3-dimensional blade shape is submitted to a mesh generator, GAMBIT, to create the mesh for the flow solver, which is FLUENT. NACA4415 airfoil is used for the blade sections. Various dihedral angles are used to make a map to determine the suitable angle that can make the wind turbine delivers the rated-power at a specified wind speed which is higher then the rated-wind speed. The results showed that the dihedral angle required at wind speed of 10 m/s is about 20°, at 11 m/s is about 25°, and at 12 m/s is about 30°. Therefore, the model of adjusting the output power by regulate the turbine blade dihedral angle suggested in this work is proved feasible.
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Books on the topic "Wing dihedral"

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Darden, Christine M. Effect of milling machine roughness and wing dihedral on the supersonic aerodynamic characteristics of a highly swept wing. Hampton, Va: Langley Research Center, 1989.

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M, Ware George, and Langley Research Center, eds. Control effectiveness and tip-fin dihedral effects for the HL-20 lifting-body configuration at Mach numbers from 1.6 to 4.5. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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Conference papers on the topic "Wing dihedral"

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Cuji, Edgar, and Ephrahim Garcia. "Aircraft Dynamics for Symmetric and Asymmetric V-Shape Morphing Wings." In ASME 2008 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2008. http://dx.doi.org/10.1115/smasis2008-424.

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This paper will present the effect of the aircraft turning dynamics for symmetric and asymmetric V-shape changing wings. The aerodynamic forces will be calculated using a 3D aerodynamic model developed that utilizes a modern adaptation of Prandtl’s lifting-line method which can be used for wings of arbitrary camber, sweep and dihedral. The method will be applied to analyze symmetric and asymmetric V-shaped wing configuration of interest for morphing aircraft application. The V-shaped wing has two sections, an out-of-plane dihedral section and a horizontal section. A study of the lift characteristics for symmetric and asymmetric with and without flap deflection will be presented. An investigation as to how the partial dihedral will affect the dynamics of the vehicle, in turning, for wings with asymmetric flap deflection is performed. An comparison of the different turning performance measurements, turning radius, bank angle, load factor, turning rate and roll moment coefficient will be presented.
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Bobbitt, Percy, Osama Kandil, and Zhi Yang. "The Benificial Effects of Wing Dihedral on Sonic Boom." In 9th AIAA/CEAS Aeroacoustics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-3273.

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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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SHANKAR, VIJAYA, and T. GOEBEL. "TREATMENT OF CLOSELY COUPLED CANARD-WING TRANSONIC FLOWS INCLUDING DIHEDRAL." In 23rd Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-428.

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Bourdin, Patrick. "Influence of Wing-tip Dihedral and Planform on Induced Drag." In World Aviation Congress & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2001. http://dx.doi.org/10.4271/2001-01-2978.

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Gili, P., and M. Battipede. "Experimental validation of the wing dihedral effect using a whirling arm equipment." In Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4194.

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Fazelzadeh, S. Ahmad, and Abbas Mazidi. "Nonlinear Equations of Motion for the Maneuvering Flexible Aircraft Wings." In ASME 2006 Pressure Vessels and Piping/ICPVT-11 Conference. ASMEDC, 2006. http://dx.doi.org/10.1115/pvp2006-icpvt-11-93623.

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In this paper, the complete dynamical equations for the general maneuvering flexible wings with sweep and dihedral angles are formulated. These equations are valid for an isotropic non-uniform wing; include transverse shear and warping effects. The equations of motion and boundary conditions are derived using Hamilton’s variational principle. Interaction between rigid-body motion caused by the angular velocities of the general maneuver, and elastic deformations of the wing, results in nonlinear terms, form an important contribution to the final equations. For model validation, the simplified partial differential equations of pull-up maneuver are transformed into a set of differential equations through a Galerkin approach and finally the results of numerical simulation are presented. The combination of flexible structural motion and maneuver parameters are very effective on natural frequencies and instability boundaries.
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Kim, Cheolwan, and Yung-Gyo Lee. "Multi-Disciplinary Design Optimization of Unmanned Aerial Vehicle." In ASME 2011 Pressure Vessels and Piping Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/pvp2011-57567.

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A general procedure of preliminary design of aircraft and one-way fluid-structure interaction (FSI) applied to aircraft design is introduced briefly. Then, FSI and optimization technique are implemented to optimize a wing shape of an unmanned aerial vehicle (UAV) for minimum cruise drag. FSI analysis and optimization processes for minimizing drag of UAV are explained. Design variables are wing taper ratio and dihedral angle, and objective function is the cruise drag of UAV. Fluid solution is generated with Euler solver and structural analysis is performed with FEM solver, Diamond. Sample points are selected by Design of Experiment (DOE) method and Kriging method is used for generation of an approximation model.
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"The effects of canard-wing flow-field interactions on longitudinal stability, effective dihedral and potential deep-stall trim." In 6th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2514.

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Guggilla, Mukesh, and Vijayakumar Rajagopalan. "CFD Investigation on the Hydrodynamic Characteristics of Blended Wing Unmanned Underwater Gliders With Emphasis on the Control Surfaces." In ASME 2020 39th International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/omae2020-19280.

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Abstract Underwater Gliders are unique buoyancy propelled oceanographic profiling vehicles. Their speed and endurance in longitudinal motion are affected by the symmetry, sweep dihedral angle and span of the control surfaces. In the low-velocity regime, these parameters can be varied to examine the flow around the glider. They also affect the lift-to-drag ratio (L/D) essential for the manoeuvring path in longitudinal and transverse motions. In this paper, the sweep angle of the main wing of a blended wing autonomous underwater glider configuration is varied as 10°, 15°, 30°, 45° and 60° and the resulting hull forms are numerically simulated in the commercial software, STARCCM+. The main wing is a tapered NACA0018 section (taken as per the general arrangement requirement) with 1.5m chord at the root and 0. 1m at the tip. The numerical model is validated using the CFD results of NACA0012 airfoil from Sun.C et al, 2015 [1]. The hydrodynamic forces are obtained by varying the angle of attack (α) of the body from −15° to 15°, for flow velocity of 0.4m/s. The hydrodynamic coefficients (lift-to-drag ratios) and flow physics around the wing are analyzed to arrive at an optimum Lift-to-drag ratio for increased endurance.
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