Relevant bibliographies by topics / Variable Camber Airfoil

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Variable Camber Airfoil'

Author: Grafiati
Published: 4 June 2021
Last updated: 15 February 2022

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Journal articles on the topic "Variable Camber Airfoil"

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Raheem, Mohammed Abdul, Prasetyo Edi, Amjad A. Pasha, Mustafa M. Rahman, and Khalid A. Juhany. "Numerical Study of Variable Camber Continuous Trailing Edge Flap at Off-Design Conditions." Energies 12, no. 16 (August 20, 2019): 3185. http://dx.doi.org/10.3390/en12163185.

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Numerical simulations are performed to study the outboard airfoil of advanced technology regional aircraft (ATRA) wings with five different variable camber continuous trailing edge flap (VCCTEF) configurations. The computational study aims to improve the aerodynamic efficiency of the airfoil under cruise conditions. The design of outboard airfoil complies with the hybrid laminar flow control design criteria. This work is unique in terms of analysis of the effects of VCCTEF on the ATRA wing’s outboard airfoil during the off-design condition. The Reynolds–Averaged Navier–Stokes equations coupled with the Spalart-Allmaras turbulence model are employed to perform the simulations for the baseline case and VCCTEF configurations. The current computational study is performed at an altitude of 10 km with a cruise Mach number of 0.77 and a Reynolds number of 2.16 × 107. Amongst all five configurations of VCCTEF airfoils studied, a flap having a parabolic profile (VCCTEF 123) configuration shows the maximum airfoil efficiency and resulted in an increase of 6.3% as compared to the baseline airfoil.
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Mesarič, Mihael, and Franc Kosel. "Unsteady airload of an airfoil with variable camber." Aerospace Science and Technology 8, no. 3 (April 2004): 167–74. http://dx.doi.org/10.1016/j.ast.2003.10.007.

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Yokozeki, Tomohiro, Aya Sugiura, and Yoshiyasu Hirano. "Development of Variable Camber Morphing Airfoil Using Corrugated Structure." Journal of Aircraft 51, no. 3 (May 2014): 1023–29. http://dx.doi.org/10.2514/1.c032573.

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Bilgen, Onur, Kevin B. Kochersberger, Daniel J. Inman, and Osgar J. Ohanian. "Novel, Bidirectional, Variable-Camber Airfoil via Macro-Fiber Composite Actuators." Journal of Aircraft 47, no. 1 (January 2010): 303–14. http://dx.doi.org/10.2514/1.45452.

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Yang, Wen-Chao, Hui Wang, Jian-Ting Yang, and Ji-Ming Yang. "Characterization of the Flow Separation of a Variable Camber Airfoil." Chinese Physics Letters 29, no. 4 (April 2012): 044701. http://dx.doi.org/10.1088/0256-307x/29/4/044701.

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Li, Xingxing, and Ke Yang. "Parametric exploration on the airfoil design space by numerical design of experiment methodology and multiple regression model." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 1 (May 17, 2019): 3–18. http://dx.doi.org/10.1177/0957650919850426.

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Robust airfoil design is crucial to efficient, stable, and safe operation for modern wind turbines. However, even for deterministic wind turbine airfoil design, the problem is complex regarding to aerodynamic, acoustic, and structural requirements of wind turbine blades. Therefore, this study aims to assess the design variable impact, identify significant variables, and obtain the correlation with the airfoil responses, to reduce the cost of the airfoil robust optimization. In this paper, the optimal hypercube design method was applied to an airfoil designed by the National Advisory Committee for Aeronautics, NACA 63-421, which is commonly employed in the outboard modern wind turbine blade, to perform the numerical design of experiments. Then, a parametric exploration on the characteristics of airfoil design space by the multiple regression model and statistical analysis method were conducted. It was identified that in regular design space, the variations of aerodynamic and structural parameters are dominated by the airfoil camber and radius of leading edge. Meanwhile, the chord-wise position of the maximum thickness also has strong impacts on the airfoil performance. In further, the overall design spaces are explored to be highly nonlinear in aerodynamic and acoustic responses because of the nonlinear effects of the airfoil chord-wise position of the maximum camber and radius of leading edge. Strong but undesirable correlations were demonstrated between the maximum lift-to-drag ratio and the total sound pressure level. These findings could serve as a valuable guidance for wind turbine airfoil robust design to screen the stochastic design variables, simplify the design space, and reduce the cost.
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Ang, Haisong, and Hongda Li. "Preliminary airfoil design of an innovative adaptive variable camber compliant wing." Journal of Vibroengineering 18, no. 3 (May 15, 2016): 1861–73. http://dx.doi.org/10.21595/jve.2016.16705.

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NIU, Wei, Yufei ZHANG, Haixin CHEN, and Miao ZHANG. "Numerical study of a supercritical airfoil/wing with variable-camber technology." Chinese Journal of Aeronautics 33, no. 7 (July 2020): 1850–66. http://dx.doi.org/10.1016/j.cja.2020.01.008.

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Bilgen, Onur, Carlos De Marqui, Kevin B. Kochersberger, and Daniel J. Inman. "Macro-Fiber Composite Actuators for Flow Control of a Variable Camber Airfoil." Journal of Intelligent Material Systems and Structures 22, no. 1 (December 21, 2010): 81–91. http://dx.doi.org/10.1177/1045389x10392613.

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Zhao, Anmin, Zou Hui, Haichuan Jin, and Dongsheng Wen. "Analysis on the Aerodynamic Characteristics of a Continuous Whole Variable Camber Airfoil." Journal of Physics: Conference Series 1215 (May 2019): 012005. http://dx.doi.org/10.1088/1742-6596/1215/1/012005.

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Dissertations / Theses on the topic "Variable Camber Airfoil"

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Li, Daxin. "Multi-objective design optimization for high-lift aircraft configurations supported by surrogate modeling." Thesis, Cranfield University, 2013. http://dspace.lib.cranfield.ac.uk/handle/1826/8468.

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Nowadays, the competition among airlines seriously depend upon the saving operating costs, with the premise that not to degrade its services quality. Especially in the face of increasingly scarce oil resources, reducing fleets operational fuel consumption, is an important means to improve profits. Aircraft fuel economy is determined by operational management strategies and application technologies. The application of technologies mainly refers to airplane’s engine performance, Weight efficiency and aerodynamic characteristics. A market competitive aircraft should thoroughly consider to all of these aspects. Transport aircraft aerodynamic performance mainly is determined by wing’s properties. Wings that are optimized for efficient flight in cruise conditions need to be fitted with powerful high-lift devices to meet lift requirements for safe takeoff and landing. These high-lift devices have a significant impact on the total airplane performance. The aerodynamic characteristics of the wing airfoil will have a direct impact on the aerodynamic characteristics of the wing, and the wing’s effective cruise hand high-lift configuration design has a significant impact on the performance of transport aircraft. Therefore, optimizing the design is a necessary airfoil design process. Nowadays engineering analysis relies heavily on computer-based solution algorithms to investigate the performance of an engineering system. Computational fluid dynamics (CFD) is one of the computer-based solution methods which are more widely employed in aerospace engineering. The computational power and time required to carry out the analysis increases as the fidelity of the analysis increases. Aerodynamic shape optimization has become a vital part of aircraft design in the recent years. Since the aerodynamic shape optimization (ASO) process with CFD solution algorithms requires a huge amount of computational power, there is always some reluctance among the aircraft researchers in employing the ASO approach at the initial stages of the aircraft design. In order to alleviate this problem, statistical approximation models are constructed for actual CFD algorithms. The fidelity of these approximation models are merely based on the fidelity of data used to construct these models. Hence it becomes indispensable to spend more computational power in order to convene more data which are further used for constructing the approximation models. The goal of this thesis is to present a design approach for assumed wing airfoils; it includes the design process, multi-objective design optimization based on surrogate modelling. The optimization design stared from a transonic single-element single-objective optimization design, and then high-lift configurations were two low-speed conditions of multi-objective optimization design, on this basis, further completed a variable camber airfoil at low speed to high-lift configuration to improve aerodynamic performance. Through this study, prove a surrogate based model could be used in the wing airfoil optimization design.
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Bilgen, Onur. "Aerodynamic and Electromechanical Design, Modeling and Implementation Of Piezocomposite Airfoils." Diss., Virginia Tech, 2010. http://hdl.handle.net/10919/28665.

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Piezoelectrics offer high actuation authority and sensing over a wide range of frequencies. A Macro-Fiber Composite is a type of piezoelectric device that offers structural flexibility and high actuation authority. A challenge with piezoelectric actuators is that they require high voltage input; however the low power consumption allows for relatively lightweight electronic components. Another challenge, for piezoelectric actuated aerodynamic surfaces, is found in operating a relatively compliant, thin structure (desirable for piezoceramic actuators) in situations where there are relatively high external (aerodynamic) forces. Establishing an aeroelastic configuration that is stiff enough to prevent flutter and divergence, but compliant enough to allow the range of available motion is the central challenge in developing a piezocomposite airfoil. The research proposed here is to analyze and implement novel electronic circuits and structural concepts that address these two challenges. Here, a detailed theoretical and experimental analysis of the aerodynamic and electromechanical systems that are necessary for a practical implementation of a piezocomposite airfoil is presented. First, the electromechanical response of Macro-Fiber Composite based unimorph and bimorph structures is analyzed. A distributed parameter electromechanical model is presented for interdigitated piezocomposite unimorph actuators. Necessary structural features that result in large electrically induced deformations are identified theoretically and verified experimentally. A novel, lightweight electrical circuitry is proposed and implemented to enable the peak-to-peak actuation of Macro-Fiber Composite bimorph devices with asymmetric voltage range. Next, two novel concepts of supporting the piezoelectric material are proposed to form two types of variable-camber aerodynamic surfaces. The first concept, a simply-supported thin bimorph airfoil, can take advantage of aerodynamic loads to reduce control input moments and increase control effectiveness. The structural boundary conditions of the design are optimized by solving a coupled fluid-structure interaction problem by using a structural finite element method and a panel method based on the potential flow theory for fluids. The second concept is a variable-camber thick airfoil with two cascading bimorphs and a compliant box mechanism. Using the structural and aerodynamic theoretical analysis, both variable-camber airfoil concepts are fabricated and successfully implemented on an experimental ducted-fan vehicle. A custom, fully automated low-speed wind tunnel and a load balance is designed and fabricated for experimental validation. The airfoils are evaluated in the wind tunnel for their two-dimensional lift and drag coefficients at low Reynolds number flow. The effects of piezoelectric hysteresis are identified. In addition to the shape control application, low Reynolds number flow control is examined using the cascading bimorph variable-camber airfoil. Unimorph type actuators are proposed for flow control in two unique concepts. Several electromechanical excitation modes are identified that result in the delay of laminar separation bubble and improvement of lift. Periodic excitation to the flow near the leading edge of the airfoil is used as the flow control method. The effects of amplitude, frequency and spanwise distribution of excitation are determined experimentally using the wind tunnel setup. Finally, the effects of piezoelectric hysteresis nonlinearity are identified for Macro-Fiber Composite bimorphs. The hysteresis is modeled for open-loop response using a phenomenological classical Preisach model. The classical Preisach model is capable of predicting the hysteresis observed in 1) two cantilevered bimorph beams, 2) the simply-supported thin airfoil, and 3) the cascading bimorph thick airfoil.
Ph. D.
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Book chapters on the topic "Variable Camber Airfoil"

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Kaul, Upender K., and Nhan T. Nguyen. "Semisupervised Learning of Lift Optimization of Multi-Element Three-Segment Variable Camber Airfoil." In Advances in Computational Intelligence and Autonomy for Aerospace Systems, 337–68. Reston ,VA: American Institute of Aeronautics and Astronautics, Inc., 2018. http://dx.doi.org/10.2514/5.9781624104794.0337.0368.

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Conference papers on the topic "Variable Camber Airfoil"

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Santhanakrishnan, Arvind, Nan Pern, and Jamey Jacob. "Optimization and Validation of a Variable Camber Airfoil." In 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-1956.

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Wright, Cody, and Onur Bilgen. "A Variable Camber Piezocomposite Trailing-Edge for Subsonic Aircraft: Multidisciplinary Design Optimization." In ASME 2019 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/smasis2019-5604.

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Abstract A continuous-surface morphing airfoil is desirable for commercial aircraft in order to improve fuel efficiency, and due to the potential to morph the wing into a high-lift configuration for take-off and landing. Piezocomposite actuators have shown to be a feasible strategy for camber morphing in small unmanned fixed-wing aircraft with a Reynold’s number in the range of 50,000 to 250,000. As an extension, this paper presents a theoretical framework and results for morphing in single and multi-segment natural laminar flow airfoils with a maximum Reynold’s number of 825,000. The airfoils presented employ a continuous inextensible surface. To achieve morphing, piezocomposite actuating elements are applied on the suction and pressure surfaces of the airfoils. The geometric properties of the airfoils are determined using a genetic algorithm optimization method with a migration strategy in order to maintain population diversity. The algorithm optimizes independently the substrate thicknesses for the nominal airfoil, the leading edge, and the piezocomposite bonded surfaces. In addition, positions and voltages for each piezocomposite actuators are optimized. The genetic algorithm uses an objective function to maximize the change in coefficient of lift to morph the airfoil from its baseline (i.e. cruise) state to the high-lift state. Analysis is performed using a coupled fluid-structure interaction method assuming static aero-elastic behavior. Optimization is followed by a parametric analysis to examine lift, drag, and lift-to-drag ratio of the airfoils over their full operational range. The optimization is performed on a symmetric, asymmetric, and the aft element of a slotted multi-segment airfoil to examine the capabilities of induced-strain actuation at high dynamic pressures.
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Bilgen, Onur, Osgar Ohanian, Kevin Kochersberger, and Daniel Inman. "Novel, Bi-Directional, Variable Camber Airfoil via Macro-Fiber Composite Actuators." In 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2133.

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DiPalma, Matthew, and Farhan Gandhi. "Directionally Variable Stiffness to Reduce Actuation Requirement in Airfoil Camber Morphing." In 24th AIAA/AHS Adaptive Structures Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1315.

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Bilgen, Onur, Erick I. Saavedra Flores, and Michael I. Friswell. "Optimization of Surface-Actuated Piezocomposite Variable-Camber Morphing Wings." In ASME 2011 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2011. http://dx.doi.org/10.1115/smasis2011-4971.

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A theoretical, two-dimensional, static-aeroelastic design, modeling and optimization of a variable-camber morphing airfoil that employs surface-induced forces via smart material actuators is presented. The structural parameters of the airfoil, mainly the substrate features, are determined using a Genetic Algorithm optimization technique. A coupled treatment of the fluid-structure interaction is employed which allows the realization of a design that is not only feasible in a bench top experiment, but that can also sustain aerodynamic loads in the wind tunnel. The substrate is assumed to be a carbon nanotube reinforced composite whose constitutive response is obtained by means of a homogenization-based multi-scale finite element model. A separate parametric study on different geometric configurations of representative volume elements is carried out for the description of the substrate material. The analyzed representative volume elements consist of a single wall carbon nanotube embedded in a soft polymer matrix.
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Kaul, Upender K., and Nhan T. Nguyen. "Lift Characterization Study of a Two-Element Three-Segment Variable Camber Airfoil." In 2018 Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-2835.

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Kaul, Upender K., and Nhan T. Nguyen. "Lift Optimization Study of a Multi-Element Three-Segment Variable Camber Airfoil." In 34th AIAA Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-3569.

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Lange, Alexander, Dean Johnson, and Nicole Key. "Section Based Profile Tolerance Assessment of 3D Scanned Compressor Airfoils." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14294.

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Abstract This paper presents two turbomachinery-specific methods for profile tolerance assessment of compressor airfoils that process 3D scan data. This optical inspection technology digitizes the entire surface of the part into a triangulated mesh, which is aligned to nominal geometry and then processed to extract densely arranged profile sections. For the reverse engineering method, the profile sections are decomposed into thickness and camber distributions. These distributions and the camber line are used to identify the profile parameter vector of the reverse engineering model. The deviation of the actual geometry is obtained by subtracting its parameters from those of the nominal geometry. Parameter-span graphs reveal airfoil shape deviation and allow for quantification of blisk scatter. The design-like parameters are meaningful and enable an intuitive engineering judgement of the actual geometry deviation. The profile tolerance assessment method utilizes the camber line from the reverse engineering method to elegantly check against variable profile tolerance limits. The actual section is best-fitted to its nominal counterpart and assessed regarding its deviation relative to the allowed local tolerance. This ratio is plotted in a developed view summarizing the result of the profile tolerance assessment for the whole airfoil in a single graph. Thus, the condensed results allow for effective utilization of the high-resolution in airfoil sections. Ultimately, the paper widens the view from one airfoil towards the assessment of the entire blisk. The blisk data is presented by statistical processing of deviation fields of all airfoils, in terms of mean and standard deviation. These statistical quantities are plotted onto the airfoil contour to e.g. represent the average airfoil thickness of the blisk. The standard deviation plot points to airfoil sections of larger geometric scatter and reveals areas of a non-robust manufacturing process.
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Wright, Cody, and Onur Bilgen. "A Piezocomposite Trailing-Edge for Subsonic Aircraft." In ASME 2018 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/smasis2018-7943.

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This paper examines the feasibility of piezocomposite morphing airfoils and trailing edge control surfaces subjected to large dynamic pressures. Piezocomposite airfoils have been shown to be feasible on small unmanned aerial vehicles, subject to relatively low dynamic pressures, operating in the Reynold’s number range of 50k to 250k. The operating range of interest in this paper has a cruising Reynold’s number range between 250k and 1M subject to relatively large wing loading. This range of Reynold’s numbers has not been explored in detail due to the large aerodynamic loads produced. Based on the authors’ previous research on small unmanned aircraft, the proposed concept is a variable-camber airfoil that employs a continuous inextensible surface and surface-bonded piezocomposite actuators. To achieve camber-morphing, multiple piezocomposite actuating elements are applied to the upper and lower surfaces. A case study is performed to determine the design parameters of the airfoil. The parameters to be varied include the substrate thickness of the baseline airfoil, leading edge, and piezocomposite bonded areas. In addition, the positions of the piezocomposites are varied. The analysis is performed using a coupled fluid-structure interaction model assuming static aeroelastic behavior. A voltage sweep is conducted on each airfoil design while being subjected to 70 m/s free stream velocity. The sweep examines the lift coefficient and lift-to-drag ratio of the airfoil over the full operational range. This research lays the groundwork for determining the feasibility of piezocomposite morphing airfoil and trailing edge concepts for use in applications subject to large dynamic pressures.
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Campanile, Lucio Flavio, and Delf Sachau. "Distributed Versus Concentrated Flexibility in Shape Control of Lifting Surfaces: The “Belt-Rib” Structural Concept." In ASME 1999 Design Engineering Technical Conferences. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/detc99/vib-8388.

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Abstract The “mechatronic” way of dealing with the issue of structure geometry control, based on mechanical systems with hinges, bearing and discrete actuators, cannot easily cope with the strict requirements of aircraft design. In this paper a “structronic” concept for airfoils with variable camber is presented, in which the desired geometry changes are achieved through structural flexibility and no moveable parts are needed. A short introduction to the “structronic” approach to structure adaptation in general and to airfoil shape control in particular opens the paper, with some emphasis on the role of solid-state actuators. The description of the new structural concept (the belt-rib concept) follows, with the application to the case of a landing flap with variable camber. Some results of FEM simulations as well as of experimental tests on different prototypes — one of them equipped with shape memory wires as actuators — are also included in the paper. The results provide a first feasibility proof of the new concept and encourage further work.
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