Bibliografías temáticas / Aircraft Wing

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Literatura académica sobre el tema "Aircraft Wing"

Autor: Grafiati

Publicado: 4 de junio de 2021

Última modificación: 2 de febrero de 2022

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Artículos de revistas sobre el tema "Aircraft Wing"

Olugbeji, Jemitola P., Okafor E. Gabriel y Godwin Abbe. "Wing Thickness Optimization for Box Wing Aircraft". Recent Patents on Engineering 14, n.º 2 (29 de octubre de 2020): 242–49. http://dx.doi.org/10.2174/1872212113666190206123755.

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Background: In the interest of improving aircraft performance, studies have highlighted the benefits of Box wing configurations over conventional cantilever aircraft configuration. Generally, the greater an aircraft's average thickness to chord ratio (τ), the lower the structural weight as well as volumetric capacity for fuel. On the other hand, the lower the ., the greater the drag reduction. A review of patents related to the Box-wing aircraft was carried out. While methodologies for optimizing wing thickness of conventional aircrafts have been studied extensively, limited research work exist on the methodology for optimizing the wing thickness to chord ratio of the Box wing aircraft configurations. Methods: To address this gap, in this work, a two stage optimization methodology based on gradient search algorithm and regression analysis was implemented for the optimization of Box wing aircrafts wing thickness to chord ratio. The first stage involved optimizing the All Up Mass (AUM), Direct Operating Cost (DOC) and Zero Lift Drag Coefficients (CDO), with respect to the aft and fore sweep angle for some selected τ values. At the second stage, a suitability function (γ) was optimized with respect to the aft and fore sweep angle for some selected τ values. A comparative study was further carried out using the proposed methodology on similar size cantilever wing aircraft. Results: From the result, an optimal τ value was reached. Also the τ value for the cantilever aircraft found based on the proposed methodology was similar to the true τ value of the adopted aircraft, thereby validating the methodology. Conclusion: Based on the optimal τ value reached from this work, the Box wing aircraft are suitable for thin airfoils.

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Sharma, Vaibhav. "Fanwing Aircraft- Scope as an Agricultural Aircraft". International Journal for Research in Applied Science and Engineering Technology 9, n.º VIII (15 de agosto de 2021): 603–7. http://dx.doi.org/10.22214/ijraset.2021.37436.

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The objective of this paper is to apply the concept of fan wing to agricultural aircrafts which are conventionally fixed wings aircrafts or multi-rotor drones. Fan wing is capable of producing good amount of lift at a sufficiently low speed without stalling, thus is apt for agricultural processes of irrigation, spraying pesticides, etc. Fan wing has a special ability that it doesn’t stalls (for the practical range of AOA), making this spraying method reliable. A fanwing aircraft is modelled using CATIA V5 and the flow visualizations for the same are performed on the ANSYS. This aircraft is then compared with three different existing agricultural aircrafts on different parameters, namely payload capacity, work efficiency and ease of operation. The comparison shows that such fanwing vehicle is a good substitute over the conventional fixed wings and multi-rotor drones.

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Siliang, Du y Tang Zhengfei. "The Aerodynamic Behavioral Study of Tandem Fan Wing Configuration". International Journal of Aerospace Engineering 2018 (30 de octubre de 2018): 1–14. http://dx.doi.org/10.1155/2018/1594570.

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The fan wing aircraft is a new concept based on a new principle, especially its wing which is based on a unique aerodynamic principle. A fan wing can simultaneously generate lift and thrust. In order to further improve its aerodynamic characteristics without changing its basic geometric parameters, two fan wings are installed along the longitudinal body, which is the composition of a tandem fan wing aircraft. Through numerical simulation, the lift and thrust of the fan wings were calculated with the distance, height, and installation angle of the front and rear fan wings changed, and the aerodynamic characteristic interaction rule between the front and rear fan wings was analyzed. In addition, the wind test model of a tandem fan wing was designed, and the results of the wind tunnel test and numerical calculation results were compared to verify the preliminary setup. The results show that at a certain height, distance, and installation angle, aerodynamic characteristics of a tandem fan wing have more advantages compared to the single fan wing. Therefore, the tandem fan wing aircraft’s advantages have good prospects for development and application.

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Hong, Wei Jiang y Dong Li Ma. "Influence of Control Coupling Effect on Landing Performance of Flying Wing Aircraft". Applied Mechanics and Materials 829 (marzo de 2016): 110–17. http://dx.doi.org/10.4028/www.scientific.net/amm.829.110.

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As flying wing aircraft has no tail and adopts blended-wing-body design, most of flying wing aircrafts are directional unstable. Pitching moment couples seriously with rolling and yawing moment when control surfaces are deflected, bringing insecurity to landing stage. Numerical simulation method and semi-empirical equation estimate method were combined to obtain a high aspect ratio flying wing aircraft’s aerodynamic coefficients. Modeling and simulation of landing stage were established by MATLAB/Simulink. The control coupling effect on lift and drag characteristics and anti-crosswind landing capability was studied. The calculation results show that when the high aspect ratio flying wing aircraft was falling into the deceleration phase, appropriate to increase the opening angle of split drag rudder can reduce the trimming pitching moment deflection of pitch flap, thereby reduce the loss of lift caused by the deflection of pitch flaps. Flying wing aircraft can be rounded out successfully by using the pitch flap gently and steady. Both side-slip method and crabbed method can be applied to the landing of high aspect ratio flying wing aircraft in crosswind, the flying wing aircraft’s anti-crosswind landing capability was weakened by the control coupling effect of split drag rudder and elevon. Sideslip method was recommended in the crosswind landing of flying wing aircraft after calculation and analysis.

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Srinivas, G. y Srinivasa Rao Potti. "Computational Analysis of Fighter Aircraft Wing under Mach Number 0.7 for Small Sweep Angles". Applied Mechanics and Materials 592-594 (julio de 2014): 1020–24. http://dx.doi.org/10.4028/www.scientific.net/amm.592-594.1020.

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Fighter aircraft wings are the leading lift generating components for any aerospace vehicle. The recital of any flying vehicle largely depends on its wing design. Missiles and the fighter aircrafts which are having propulsion system mostly have fins to control and maneuver. In this present paper work an attempt has been made to design a fighter aircraft wing configuration which will be used in some air launched air to surface guided weapons fighter aircraft. The main focus of this paper agreement in determining the Sweep-back effects on fighter aircraft wing under transonic condition at different angles of attack (AoA) from 0 to 5 degrees. For this the fighter aircraft wing performance for various flow conditions and sweep angles are obtained based on the empirical, semi-empirical and CFD simulation results. Hence by studying these computational results would help in the optimizing geometry for better performance, an finest wing design for the air launched air to surface body with conservative wing can be obtained.

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Jemitola, P. O., G. Monterzino y J. Fielding. "Wing mass estimation algorithm for medium range box wing aircraft". Aeronautical Journal 117, n.º 1189 (marzo de 2013): 329–40. http://dx.doi.org/10.1017/s0001924000008022.

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Abstract A procedure for defining an empirical formula for the mass estimation of the fore and aft wings field Uof a medium range box wing aircraft is described. The procedure is based upon the work of Howe for estimating the wing mass of conventional cantilever wing aircraft. The paper outlines the procedure used to relate conventional cantilever wings to box wing aircraft wings. Using a vortex lattice tool, finite element methods and regression analysis, the modification performed on the coefficient in Howe’s method to enable its use on a medium range box wing aircraft is outlined. The results show that the fore and aft wings would use the same correction coefficient and that the aft wing would therefore be lighter than the fore wing on a medium range box wing aircraft.

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Teo, Z. W., T. H. New, Shiya Li, T. Pfeiffer, B. Nagel y V. Gollnick. "Wind tunnel testing of additive manufactured aircraft components". Rapid Prototyping Journal 24, n.º 5 (9 de julio de 2018): 886–93. http://dx.doi.org/10.1108/rpj-06-2016-0103.

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Purpose This paper aims to report on the physical distortions associated with the use of additive manufactured components for wind tunnel testing and procedures adopted to correct for them. Design/methodology/approach Wings of a joined-wing test aircraft configuration were fabricated with additive manufacturing and tested in a subsonic closed-loop wind tunnel. Wing deflections were observed during testing and quantified using image-processing procedures. These quantified deflections were then incorporated into numerical simulations and results had agreed with wind tunnel measurement results. Findings Additive manufacturing provides cost-effective wing components for wind tunnel test components with fast turn-around time. They can be used with confidence if the wing deflections could be accounted for systematically and accurately, especially at the region of aerodynamic stall. Research limitations/implications Significant wing flutter and unsteady deflections were encountered at higher test velocities and pitch angles. This reduced the accuracy in which the wing deflections could be corrected. Additionally, wing twists could not be quantified as effectively because of camera perspectives. Originality/value This paper shows that additive manufacturing can be used to fabricate aircraft test components with satisfactory strength and quantifiable deflections for wind tunnel testing, especially when the designs are significantly complex and thin.

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Andrews, SA y RE Perez. "Analytic study of the conditions required for longitudinal stability of dual-wing aircraft". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, n.º 5 (11 de mayo de 2017): 958–72. http://dx.doi.org/10.1177/0954410017704215.

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Recent studies of new, fuel-efficient transport aircraft have considered designs, which make use of two principal lifting surfaces to provide the required lift as well as trim and static stability. Such designs include open tandem-wings as well as closed joined and box-wings. As a group, these aircraft can be termed dual-wing designs. This study developed a new analytic model, which takes into account the downwash from the two main wings and is sensitive to three important design variables: the relative areas of each wing, the streamwise separation of the wings, and the center of gravity position. This model was used to better understand trends in the dual-wing geometry on the stability, maneuverability, and lift-to-drag ratio of the aircraft. Dual-wing aircraft have been shown to have reduced the induced drag compared to the conventional designs. In addition, further drag reductions can be realized as the horizontal tail can be removed if the dual-wings have sufficient streamwise stagger to provide the moments necessary for trim and longitudinal stability. As both wings in a dual-wing system carry a significant fraction of the total lift, trends in such designs that led to longitudinal stability can differ from those of the conventional aircraft and have not been the subject of detailed investigation. Results from the analytic model showed that the longitudinal stability required either a reduction of the fore wing area or shifting the center of gravity forward from the midpoint of both wings' aerodynamic centers. In addition, for wing configurations of approximately equal fore and aft wing areas, increasing the separation between the two wings decreased the stability of the aircraft. The source of this unusual behavior was the asymmetric distribution of downwash upstream and downstream of the wing. These relationships between dual-wing geometry and stability will provide initial guidance on the conceptual design of dual-wing aircraft and aid in the understanding of the results of more complex studies of such designs, furthering the development of future transport aircraft.

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Kalinowski, Miłosz. "Aero-Structural Optimization of Joined-Wing Aircraft". Transactions on Aerospace Research 2017, n.º 4 (1 de diciembre de 2017): 48–63. http://dx.doi.org/10.2478/tar-2017-0028.

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Abstract Joined-wing aircraft due to its energy characteristics is a suitable configuration for electric aircraft when designed properly. However, because of the specific for this aircraft phenomenons (e.g. static indeterminacy of structure, aerodynamic interference of lifting surfaces) it demands more complicated methods to model its behavior than a traditional aircraft configurations. For these reasons the aero-structural optimization process is proposed for joined-wing aircrafts that is suitable for preliminary design. The process is a global search, modular algorithm based on automatic geometry generator, FEM solver and aerodynamic panel method. The range of aircraft was assumed as an objective function. The algorithm was successfully tested on UAV aircraft. The improvement of 19% of total aircraft range is achieved in comparison to baseline aircraft. Time of evaluation of this global search algorithm is similar to the time characteristic for local optimization methods. It allows to reduce the time and costs of preliminary design of joined-wing.

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Teng, Xichao, Qifeng Yu, Jing Luo, Xiaohu Zhang y Gang Wang. "Pose Estimation for Straight Wing Aircraft Based on Consistent Line Clustering and Planes Intersection". Sensors 19, n.º 2 (16 de enero de 2019): 342. http://dx.doi.org/10.3390/s19020342.

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Aircraft pose estimation is a necessary technology in aerospace applications, and accurate pose parameters are the foundation for many aerospace tasks. In this paper, we propose a novel pose estimation method for straight wing aircraft without relying on 3D models or other datasets, and two widely separated cameras are used to acquire the pose information. Because of the large baseline and long-distance imaging, feature point matching is difficult and inaccurate in this configuration. In our method, line features are extracted to describe the structure of straight wing aircraft in images, and pose estimation is performed based on the common geometry constraints of straight wing aircraft. The spatial and length consistency of the line features is used to exclude irrelevant line segments belonging to the background or other parts of the aircraft, and density-based parallel line clustering is utilized to extract the aircraft’s main structure. After identifying the orientation of the fuselage and wings in images, planes intersection is used to estimate the 3D localization and attitude of the aircraft. Experimental results show that our method estimates the aircraft pose accurately and robustly.

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Tesis sobre el tema "Aircraft Wing"

McKechnie, Gregor. "Wing Design for the ECO1 Aircraft". Thesis, KTH, Flygdynamik, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-180460.

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An analysis of a new wing for the ECO1 general aviation aircraft. A new wing for this aircraft is hoped to provide better high-lift performance and a higher maximum angle of attack. To this end, using computational fluid dynamics with the SST k-ω turbulence model, this study explores modifying the wing profile and augmenting the wings with winglets, a feature not commonly used in general aviation. Using the CFD tool Fluent, two-dimensional simulations on variations of the Osquavia aerofoil indicate that both the slimmer and the elongated variants will provide for a greater maximum coefficient of lift and a higher stall angle. The three-dimensional CFD analysis predict that the winglets will decrease the overall drag in high lift-coefficient flight conditions without greatly penalising performance in the cruise condition. The addition of winglets are also shown to provide a higher angle of stall and improve flow across the control surfaces at high angles of attack.

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Go, Tiauw Hiong. "Aircraft wing rock dynamics and control". Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/50081.

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Thesis (Sc.D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.
Includes bibliographical references (p. 232-236).
The dynamics of wing rock on rigid aircraft having single, two, and three rotational degrees-of-freedom are analyzed. For the purpose of the analysis, nonlinear mathematical models of the aircraft are developed. The aerodynamic expressions contained in the models can be built by fitting the appropriate aerodynamic data into the model. The dynamic analysis is performed analytically using a technique combining the Multiple Time Scales method, Center Manifold Reduction principle, and bifurcation theory. The technique yields solutions in parametric forms and leads to the separation of fast and slow dynamics, and a great insight into the system behavior. Further, a unified framework for the investigation of wing rock dynamics and control of aircraft is developed. Good agreement between the analytical results and the numerical simulations is demonstrated. Based on the results of the dynamic analysis, appropriate control strategies for the wing rock alleviation are developed. The control power limitation of the conventional aerodynamics control surfaces is considered and its effects on the alleviation of wing rock are investigated. Finally, the potential use of advanced controls to overcome the conventional controls limitation is discussed.
by Tiauw Hiong Go.
Sc.D.

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Huang, Haidong. "Optimal design of a flying-wing aircraft inner wing structure configuration". Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7439.

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Flying-wing aircraft are considered to have great advantages and potentials in aerodynamic performance and weight saving. However, they also have many challenges in design. One of the biggest challenges is the structural design of the inner wing (fuselage). Unlike the conventional fuselage of a tube configuration, the flying-wing aircraft inner wing cross section is limited to a noncircular shape, which is not structurally efficient to resist the internal pressure load. In order to solve this problem, a number of configurations have been proposed by other designers such as Multi Bubble Fuselage (MBF), Vaulted Ribbed Shell (VLRS), Flat Ribbed Shell (FRS), Vaulted Shell Honeycomb Core (VLHC), Flat Sandwich Shell Honeycomb Core (FLHC), Y Braced Box Fuselage and the modified fuselage designed with Y brace replaced by vaulted shell configurations. However all these configurations still inevitably have structural weight penalty compared with optimal tube fuselage layout. This current study intends to focus on finding an optimal configuration with minimum structural weight penalty for a flying-wing concept in a preliminary design stage. A new possible inner wing configuration, in terms of aerodynamic shape and structural layout, was proposed by the author, and it might be referred as ‘Wave-Section Configuration’. The methodologies of how to obtain a structurally efficient curvature of the shape, as well as how to conduct the initial sizing were incorporated. A theoretical analysis of load transmission indicated that the Wave-Section Configuration is feasible, and this was further proved as being practical by FE analysis. Moreover, initial FE analysis and comparison of the Wave-Section Configuration with two other typical configurations, Multi Bubble Fuselage and Conventional Wing, suggested that the Wave-Section Configuration is an optimal design in terms of weight saving. However, due to limitations of the author’s research area, influences on aerodynamic performances have not yet been taken into account.

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Andersson, Daniel. "The performance of an iced aircraft wing". Thesis, Högskolan Väst, Institutionen för ingenjörsvetenskap, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:hv:diva-4098.

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The goal of this thesis work has been to develop and manufacture an ice layer which was to be mounted on the tip of a scaled down wing model. The iced wing should be tested in a wind tunnel and aerodynamic comparisons should be made to the same wing without ice.The development of the ice was carried out as a modified product development process. The main differences are that there is no costumer and that the actual shape and functions of the product are more or less predetermined. The challenge was to find the best way to create the ice layer and how to mount it to the wing without damaging it or covering any pressure sensors. Product development methods such as pros and cons lists and prototypes were used to solve problems before printing the plastic ice layer in a rapid prototyping machine.Wind tunnel experiments were then conducted on the wing with and without the manufactured ice. Raw data from the wind tunnel were processed and lift and drag coefficients were calculated using mathematical equations. Finally, conclusions were drawn by comparing the results from the wind tunnel tests with theory, other works as well as CFD simulations.The ice layer was successfully manufactured and it met the target specifications. The aerodynamic performance of an iced aircraft wing proved to be considerably worse compared to a blank wing. The maximum achievable lift force decreased by 22% and an increased drag force will require more thrust from the airplane.

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Xia, YuXin M. B. A. Sloan School of Management. "M28 Fixed wing transport aircraft cost reduction". Thesis, Massachusetts Institute of Technology, 2011. http://hdl.handle.net/1721.1/66038.

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Thesis (M.B.A.)--Massachusetts Institute of Technology, Sloan School of Management; and, (S.M.)--Massachusetts Institute of Technology, Engineering Systems Division; in conjunction with the Leaders for Global Operations Program at MIT, 2011.
Cataloged from PDF version of thesis.
Includes bibliographical references (p. 146-148).
The M28 is a Polish short-takeoff-and-landing (STOL) light cargo aircraft developed in 1984 and currently built by PZL Mielec, a subsidiary of United Technology Corporation (UTC). There has been renewed interest in the product from military and commercial markets due to its impressive STOL capabilities. However, in order to become price-competitive, its cost would need to be reduced significantly. Multiple cost-reduction concepts have been proposed by the manufacturing and procurement groups. An Optimization Team was also formed to lead the cost-reduction effort. However, a more systematic approach is required in order to achieve the ambitious reduction goals. The proposed solution is to create a top-down systematic cost-reduction framework used to coordinate and prioritize the team's current bottom-up approach. A top-down cost reduction strategy was developed based on UTC Otis' Octopus Fishing concept. Such methodology, heavily finance driven, systematically breaks M28 into sub-systems, and prioritizes improvement recommendations based on cost-reduction potentials. It also leverages on the wealth of knowledge from global cross-functional teams to generate explosive amount of improvement recommendations. The sub-systems were benchmarked against competitors cost structures. The framework will be linked to concepts generated from the database to create a process that combine top-down and bottom-up approaches. After tasks were prioritized using the outlined framework, a three-prong approach was implemented to enhance cost reduction capability. Manufacturing of labor intensive parts such as nacelle deflection cover was automated using CNC machines. A set of commodity purchasing strategies were formulated for forgings, avionics, raw materials, interior and composite materials. Lastly, a discrete Kaizen event was described to aid redesign-for-manufacturing.
by Yuxin Xia.
S.M.
M.B.A.

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Miao, Zhisong. "Aircraft engine performance and integration in a flying wing aircraft conceptual design". Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7249.

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The increasing demand of more economical and environmentally friendly aero engines leads to the proposal of a new concept – geared turbofan. In this thesis, the characteristics of this kind of engine and relevant considerations of integration on a flying wing aircraft were studied. The studies can be divided into four levels: GTF-11 engine modelling and performance simulation; aircraft performance calculation; nacelle design and aerodynamic performance evaluation; preliminary engine installation. Firstly, a geared concept engine model was constructed using TURBOMATCH software. Based on parametric analysis and SFC target, the main cycle parameters were selected. Then, the maximum take-off thrust was verified and corrected from 195.56kN to 212kN to meet the requirements of take-off field length and second segment climb. Besides, the engine performance at offdesign points was simulated for aircraft performance calculation. Secondly, an aircraft performance model was developed and the performance of FW-11 was calculated on the basis of GTF-11 simulation results. Then, the effect of GTF-11 characteristics performance on aircraft performance was evaluated. A comparison between GTF-11 and conventional turbofan, RB211- 524B4, indicated that the aircraft can achieve a 13.1% improvement in fuel efficiency by using the new concept engine. Thirdly, a nacelle was designed for GTF-11 based on NACA 1-series and empirical methods while the nacelle dimensions of conventional turbofan RB211-525B4 were obtained by measure approach. Then, the installation thrust losses caused by nacelle drags of the two engines were evaluated using ESDU 81024a. The results showed that the nacelle drags account for about 4.08% and 3.09% of net thrust for GTF-11 and RB211-525B4, respectively. Finally, the considerations of engine installation on a flying wing aircraft were discussed and a preliminary disposition of GTF-11 on FW-11 was presented.

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Mesrobian, Chris Eden. "Concept Study of a High-Speed, Vertical Take-Off and Landing Aircraft". Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/35574.

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The purpose of the study was to evaluate the merits of the DiscRotor concept that combine the features of a retractable rotor system for vertical take-off and landing (VTOL) with an integral, circular wing for high-speed flight. Tests were conducted to generate basic aerodynamic characteristics of the DiscRotor in hover and in fixed-wing flight.

To assess the DiscRotor during hover, small scale tests were conducted on a 3ft diameter rotor without the presence of a fuselage. A â hover rigâ was constructed capable of rotating the model rotor at speeds up to 3,500 RPM to reach tip speeds of 500fps. Thrust and torque generated by the rotating model were measured via a two-component load cell, and time averaged values were obtained for various speeds and pitch angles. It has been shown that the DiscRotor will perform well in hover. Ground Effects in hover were examined by simulating the ground with a movable, solid wall. The thrust was found to increase by 50% compared to the ground-independent case. Pressure distributions were measured on the ground and disc surfaces. Velocity measurements examined the flow field downstream of the rotor by traversing a seven hole velocity probe. A wake behind the rotor was shown to contract due to a low pressure region that develops downstream of the disc.

Wind tunnel experimentation was also performed to examine the fixed wing flight of the DiscRotor. These experiments were performed in the VA Tech 6â X6â Stability Tunnel. A model of the fuselage and a circular wing was fabricated based upon an initial sizing study completed by our partners at Boeing. Forces were directly measured via a six degree of freedom load cell, or balance, for free stream velocities up to 200fps. Reynolds numbers of 2 and 0.5 million have been investigated for multiple angles of attack. Low lift-to-drag ratios were found placing high power requirements for the DiscRotor during fixed-wing flight. By traversing a seven-hole velocity probe, velocities in a 2-D grid perpendicular to the flow were measured on the model. The strengths of shed vortices from the model were calculated. A method to improve fixed-wing performance was considered where two blades were extended from the disc. An increase of 0.17 in the CL was measured due to the interaction between the disc and blades.

This research utilized a wide range of experiments, with the aim of generating basic aerodynamic characteristics of the DiscRotor. A substantial amount of quantitative data was collected that could not be included in this document. Results aided in the initial designs of this aircraft for the purpose of evaluating the merit of the DiscRotor concept.
Master of Science

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Ikeda, Toshihiro y toshi ikeda@gmail com. "Aerodynamic Analysis of a Blended-Wing-Body Aircraft Configuration". RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2006. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20070122.163030.

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In recent years unconventional aircraft configurations, such as Blended-Wing-Body (BWB) aircraft, are being investigated and researched with the aim to develop more efficient aircraft configurations, in particular for very large transport aircraft that are more efficient and environmentally-friendly. The BWB configuration designates an alternative aircraft configuration where the wing and fuselage are integrated which results essentially in a hybrid flying wing shape. The first example of a BWB design was researched at the Loughead Company in the United States of America in 1917. The Junkers G. 38, the largest land plane in the world at the time, was produced in 1929 for Luft Hansa (present day; Lufthansa). Since 1939 Northrop Aircraft Inc. (USA), currently Northrop Grumman Corporation and the Horten brothers (Germany) investigated and developed BWB aircraft for military purposes. At present, the major aircraft industries and several universities has been researching the BWB concept aircraft for civil and military activities, although the BWB design concept has not been adapted for civil transport yet. The B-2 Spirit, (produced by the Northrop Corporation) has been used in military service since the late 1980s. The BWB design seems to show greater potential for very large passenger transport aircraft. A NASA BWB research team found an 800 passenger BWB concept consumed 27 percent less fuel per passenger per flight operation than an equivalent conventional configuration (Leiebeck 2005). The purpose of this research is to assess the aerodynamic efficiency of a BWB aircraft with respect to a conventional configuration, and to identify design issues that determine the effectiveness of BWB performance as a function of aircraft payload capacity. The approach was undertaken to develop a new conceptual design of a BWB aircraft using Computational Aided Design (CAD) tools and Computational Fluid Dynamics (CFD) software. An existing high-capacity aircraft, the Airbus A380 Contents RMIT University, Australia was modelled, and its aerodynamic characteristics assessed using CFD to enable comparison with the BWB design. The BWB design had to be compatible with airports that took conventional aircraft, meaning a wingspan of not more than 80 meters for what the International Civil Aviation Organisation (ICAO) regulation calls class 7 airports (Amano 2001). From the literature review, five contentions were addressed; i. Is a BWB aircraft design more aerodynamically efficient than a conventional aircraft configuration? ii. How does the BWB compare overall with a conventional design configuration? iii. What is the trade-off between conventional designs and a BWB arrangement? iv. What mission requirements, such as payload and endurance, will a BWB design concept become attractive for? v. What are the practical issues associated with the BWB design that need to be addressed? In an aircraft multidisciplinary design environment, there are two major branches of engineering science; CFD analysis and structural analysis; which is required to commence producing an aircraft. In this research, conceptual BWB designs and CFD simulations were iterated to evaluate the aerodynamic performance of an optimal BWB design, and a theoretical calculation of structural analysis was done based on the CFD results. The following hypothesis was prompted; A BWB configuration has superior in flight performance due to a higher Lift-to-Drag (L/D) ratio, and could improve upon existing conventional aircraft, in the areas of noise emission, fuel consumption and Direct Operation Cost (DOC) on service. However, a BWB configuration needs to employ a new structural system for passenger safety procedures, such as passenger ingress/egress. The research confirmed that the BWB configuration achieves higher aerodynamic performance with an achievement of the current airport compatibility issue. The beneficial results of the BWB design were that the parasite drag was decreased and the spanwise body as a whole can generate lift. In a BWB design environment, several advanced computational techniques were required to compute a CFD simulation with the CAD model using pre-processing and CFD software.

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Zan, Steven James. "An investigation of low-speed wing buffet". Thesis, University of Cambridge, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.358845.

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Qiao, Yuqing. "Effect of wing flexibility on aircraft flight dynamics". Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7280.

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The purpose of this thesis is to give a preliminary investigation into the effect of wing deformation on flight dynamics. The candidate vehicle is FW-11 which is a flying wing configuration aircraft with high altitude and long endurance characteristics. The aeroelastic effect may be significant for this type of configuration. Two cases, the effect of flexible wing on lift distribution and on roll effectiveness during the cruise condition with different inertial parameters are investigated. For the first case, as the wing bending and twisting depend on the interaction between the wing structural deflections and the aerodynamic loads, the equilibrium condition should be calculated. In order to get that condition, mass, structure characteristics and aerodynamic characteristics are estimated first. Then load model and aerodynamic model are built. Next the interaction calculation program is applied and the equilibrium condition of the aircraft is calculated. After that, effect of wing flexibility on lift parameters is investigated. The influence of CG, location of lift and location of flexural axis are investigated. The other case is to calculate the transient roll rate response and estimate the rolling effectiveness of flexible aircraft, and compared with the rigid aircraft’s. A pure roll model is built and derivatives both for the rigid wing and the flexible wing are estimated. It has been found that flexible wing leads to the loss of control effectiveness, even cause reversal when reduces the structure natural frequency. The influence of inertia data for flexible roll is also investigated.

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Libros sobre el tema "Aircraft Wing"

Keane, Andrew J., András Sóbester y James P. Scanlan. Small Unmanned Fixed-wing Aircraft Design. Chichester, UK: John Wiley & Sons, Ltd, 2017. http://dx.doi.org/10.1002/9781119406303.

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Bolonkin, Alexander. Estimated benefits of variable-geometry wing camber control for transport aircraft. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

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Drain, Richard. 5th Bomb Wing: History of aircraft assigned. [S.l.]: R.E. Drain, 1991.

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Pantham, Satyaraj. Classical dynamics of variable sweep wing aircraft. Bangalore, India: Dept. of Aerospace Engineering, Indian Institute of Science, 1993.

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Phillips, James D. Modal control of an oblique wing aircraft. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

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Kroo, Ilan. The aerodynamic design of oblique wing aircraft. New York: American Institute of Aeronautics and Astronautics, 1986.

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Jan, Koniarek, ed. Poland's PZL gull-wing fighters: Part One: P.1 through P.8. St. Paul, Minnesota: Phalanx Publishing Company, 1995.

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Smith, Peter J. Damage tolerant composite wing panels for transport aircraft. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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Martin, John. On a wing and a microwave. [S.l.]: [s.n.], 1988.

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Capítulos de libros sobre el tema "Aircraft Wing"

Hörnschemeyer, R., G. Neuwerth y R. Henke. "Influencing Aircraft Wing Vortices". En Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 181–204. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-04088-7_8.

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Howe, Denis. "Configuration of the Wing". En Aircraft Conceptual Design Synthesis, 113–38. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch5.

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Nicolosi, F., V. Cusati, D. Ciliberti, Pierluigi Della Vecchia y S. Corcione. "Aeroelastic Wind Tunnel Tests of the RIBES Wing Model". En Flexible Engineering Toward Green Aircraft, 9–28. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-36514-1_2.

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Breuer, Ulf Paul. "Tailored Wing Design and Panel Case Study". En Commercial Aircraft Composite Technology, 179–212. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-31918-6_8.

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Ren, Beibei, Shuzhi Sam Ge, Chang Chen, Cheng-Heng Fua y Tong Heng Lee. "Stability Analysis for Rotary-Wing Aircraft". En Modeling, Control and Coordination of Helicopter Systems, 41–58. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4614-1563-3_3.

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Verrastro, Maurizio y Sylvain Metge. "Morphing Wing Integrated Safety Approach and Results". En Smart Intelligent Aircraft Structures (SARISTU), 43–69. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_2.

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Nagel, Christof, Arne Fiedler, Oliver Schorsch y Andreas Lühring. "Seamless Morphing Concepts for Smart Aircraft Wing Tip". En Smart Intelligent Aircraft Structures (SARISTU), 275–91. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_14.

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"Wing Design". En Aircraft Design, 161–264. Chichester, UK: John Wiley & Sons, Ltd, 2012. http://dx.doi.org/10.1002/9781118352700.ch5.

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"From Tube and Wing to Flying Wing". En Advanced Aircraft Design, 121–55. Oxford, UK: John Wiley & Sons, Ltd, 2013. http://dx.doi.org/10.1002/9781118568101.ch5.

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Green, Nicholas, Steven Gaydos, Hutchison Ewan y Edward Nicol. "Fixed wing aircraft". En Handbook of Aviation and Space Medicine, 1–3. CRC Press, 2019. http://dx.doi.org/10.1201/9780429021657-1.

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Actas de conferencias sobre el tema "Aircraft Wing"

Yang, Jian, Pia Sartor, Jonathan E. Cooper y R. K. Nangia. "Morphing Wing Design for Fixed Wing Aircraft". En 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-0441.

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Vedantam, Mihir, Shahriar Keshmiri, Gonzalo Garcia y Weizhang Huang. "Fixed Wing Aircraft Perching". En AIAA Guidance, Navigation, and Control Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-1915.

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Manzo, Justin E., Emily A. Leylek y Ephrahim Garcia. "Drawing Insight From Nature: A Bat Wing for Morphing Aircraft". En ASME 2008 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2008. http://dx.doi.org/10.1115/smasis2008-613.

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Being the only flying mammal, bats have evolved unique flight devices affording them high maneuverability and efficiency despite their low flight speeds. By selecting bats of three different ecological niches — a highly efficient fishing bat, a nimble insectivorous forager, and a large soaring bat of the ‘flying fox’ family — passive wing shapes can be demonstrated as capable of attaining very different aerodynamic performance characteristics. The aerodynamics of man-made equivalents to these wing shapes, using thin airfoils rather than skeleton and membrane construction, are studied both computationally through a lifting-line approach and experimentally with quasistatic wind tunnel data of ‘morphed’ and ‘unmorphed’ wing shapes. Results confirm that shape inspired by the larger soaring bat has higher lift-to-drag ratios, while that of the foraging bat maintains lift at higher angles of attack than the other wings. The advantages are more pronounced by morphing, increasing both lift coefficient and lift-to-drag ratios by up to 50% for certain wings. This is validated both numerically and in the Cornell University 4′×4′ wind tunnel. Analysis of these shapes provides the first phase of wing design for use on a morphing aircraft vehicle. In order to take greater advantage of vehicle morphing, wing shapes with camber and twist distributions unique from those found in nature will evolve to suit a man-made structure. In this way, a wing shape intended for cruise may extend its practicality into highly maneuverable operations through the use of wing morphing. Starting from the bat planform shapes, a series of optimizations determines the best camber and twist distributions for effective morphing. Given a fixed degree of shape change at any point along an airfoil based on mechanism constraints, improved morphing performance can be found compared to initial assumptions of the natural shape change. Heuristic optimization employing simulated annealing determines the required morphing shapes for increased performance, broadening the abilities of each wing shape by increasing parameters such as lift, rolling moment, and endurance.

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Balmer, Georg, Tin Muskardin, Sven Wlach y Konstantin Kondak. "Enhancing Model-Free Wind Estimation for Fixed-Wing UAV". En 2018 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2018. http://dx.doi.org/10.1109/icuas.2018.8453419.

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Ma, Chao y Lixin Wang. "Flying-Wing Aircraft Control Allocation". En 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-55.

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Dizdarevic, Michael. "Longitudinal Double Wing (LDW) Aircraft". En 2013 International Powered Lift Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-4325.

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XIE, Rong, Kairui ZHAO, Yuyan CAO y Ting LI. "Quantitative Estimation of Wing Damage for Fixed-wing Aircraft". En 2020 39th Chinese Control Conference (CCC). IEEE, 2020. http://dx.doi.org/10.23919/ccc50068.2020.9189233.

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Britt, Robert, Daniel Ortega, John Mc Tigue y Matthew Scott. "Wind Tunnel Test of a Very Flexible Aircraft Wing". En 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
20th AIAA/ASME/AHS Adaptive Structures Conference
14th AIAA. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-1464.

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Cook, Harold R. "Contour Assessment of Formed Wing Panels". En General Aviation Aircraft Meeting and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1985. http://dx.doi.org/10.4271/850884.

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Roehl, Peter, Dimitri Mavris y Daniel Schrage. "HSCT wing design through multilevel decomposition". En Aircraft Engineering, Technology, and Operations Congress. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3944.

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Informes sobre el tema "Aircraft Wing"

ITT SYSTEMS ROME NY. Rotary Wing Aircraft Crash Resistance. Fort Belvoir, VA: Defense Technical Information Center, mayo de 1987. http://dx.doi.org/10.21236/ada396019.

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Kominek, Allen K. y Harry T. Shamansky. Sub-Aperture Antenna Modeling on Fixed Wing Aircraft. Fort Belvoir, VA: Defense Technical Information Center, julio de 2001. http://dx.doi.org/10.21236/ada397118.

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Wentworth, Sean L., Everette McGowin, Ivey II, Rash Rebecca H., McLean Clarence E. y William E. Transmittance Characteristics of U.S. Army Rotary-Wing Aircraft Transparencies. Fort Belvoir, VA: Defense Technical Information Center, marzo de 1995. http://dx.doi.org/10.21236/ada296675.

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Leonard, Norman J. y III. Wing in Ground Effect Aircraft: An Airlifter of the Future. Fort Belvoir, VA: Defense Technical Information Center, junio de 2001. http://dx.doi.org/10.21236/ada430859.

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Efroymson, R. A. Ecological Risk Assessment Framework for Low-Altitude Overflights by Fixed-Wing and Rotary-Wing Military Aircraft. Office of Scientific and Technical Information (OSTI), enero de 2001. http://dx.doi.org/10.2172/777698.

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Rash, C., C. Suggs, P. LeDuc, G. Adam y S. Manning. Accident Rates in Glass Cockpit Model U.S. Army Rotary-Wing Aircraft. Fort Belvoir, VA: Defense Technical Information Center, agosto de 2001. http://dx.doi.org/10.21236/ada396085.

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Mertaugh, Lawrence J. Naval Rotary Wing Aircraft Flight Test Squadron Flight Test Approval Process. Fort Belvoir, VA: Defense Technical Information Center, enero de 1998. http://dx.doi.org/10.21236/ada350674.

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Harvey, Walter B. y Charles M. Ryan. A Quantitative Analysis of the Benefits of Prototyping Fixed-Wing Aircraft. Fort Belvoir, VA: Defense Technical Information Center, junio de 2012. http://dx.doi.org/10.21236/ada563152.

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Branson, Roger, Robert Anschuetz, Karen Bourgeois y Paul Kelly. Advanced Distributed Simulation Technology Advanced Rotary Wing Aircraft. Software Reusability Report. Fort Belvoir, VA: Defense Technical Information Center, abril de 1994. http://dx.doi.org/10.21236/ada280434.

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Swanson, Carl, Karen Humber, Rick Bright, Maria Ipsaro y Pete Peterson. ADST Version Description Document for the Rotary Wing Aircraft, BDS-D 1.0.0. Fort Belvoir, VA: Defense Technical Information Center, noviembre de 1992. http://dx.doi.org/10.21236/ada282817.

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