Relevant bibliographies by topics / Lift (Aerodynamics) Airplanes

Contents

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

Academic literature on the topic 'Lift (Aerodynamics) Airplanes'

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

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Journal articles on the topic "Lift (Aerodynamics) Airplanes"

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bin Abu Bakar, Mohd Ridh, Bambang Basuno, and Sulaiman Hasan. "Aerodynamics Analysis on Unsymmetrical Fuselage Models." Applied Mechanics and Materials 315 (April 2013): 273–77. http://dx.doi.org/10.4028/www.scientific.net/amm.315.273.

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The large commercial passengers airplanes are mostly designed to have symmetrical body with respect to the longitudinal axis. However for small passengers airplanes or for the airplane designed as UAV plat form is normally having an unsymmetrical fuselage. The aerodynamics characteristics fuselage may give a strong influence to the overall aerodynamics characteristics of the airplane. The present work investigates the aerodynamics characteristics of the unsymmetrical fuselage with respect to the longitudinal axis. The fuselage assumed to have circular cross section and the coordinate of the fu
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Secco, Ney Rafael, and Bento Silva de Mattos. "Artificial neural networks to predict aerodynamic coefficients of transport airplanes." Aircraft Engineering and Aerospace Technology 89, no. 2 (2017): 211–30. http://dx.doi.org/10.1108/aeat-05-2014-0069.

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Purpose Multidisciplinary design frameworks elaborated for aeronautical applications require considerable computational power that grows enormously with the utilization of higher fidelity tools to model aeronautical disciplines like aerodynamics, loads, flight dynamics, performance, structural analysis and others. Surrogate models are a good alternative to address properly and elegantly this issue. With regard to this issue, the purpose of this paper is the design and application of an artificial neural network to predict aerodynamic coefficients of transport airplanes. The neural network must
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Karpuk, Stanislav, Snorri Gudmundsson, and Vladimir Golubev. "Feasibility Study of a Multi-Purpose Aircraft Concept with a Leading-Edge Embedded Cross-Flow Fan." Unmanned Systems 08, no. 01 (2020): 21–32. http://dx.doi.org/10.1142/s2301385020500028.

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The research presented focuses on investigating the use of Cross-Flow Fan (CFF) as a high-lift device for a Short Take-off and Landing (STOL) aircraft. The wing-embedded fan performance analysis is mostly addressed from an aerodynamic perspective and focuses on using such Active Flow Control (AFC) technology in the conceptual aircraft design process. In particular, the design trade study of an aircraft featuring the fan as a high-lift device applied to a conceptual design of a medium-range multi-purpose aircraft is performed. A sensitivity analysis is employed to investigate the impact of the
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Rostami, M., and SA Bagherzadeh. "Development and validation of an enhanced semi-empirical method for estimation of aerodynamic characteristics of light, propeller-driven airplanes." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 4 (2016): 638–48. http://dx.doi.org/10.1177/0954410016683415.

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This study is intended to introduce an enhanced semi-empirical method for estimation of longitudinal and lateral-directional stability and control derivatives in the preliminary design phase of light airplanes. Specialised for light, single or twin propeller-driven airplanes, available state-of-the-art analytical procedures and design data compendia are combined and modified in a unique compatible method, and automated in NAMAYEH software. In the present study, modified procedures and the software structure are presented. Afterwards, the proposed method is applied to a four-place, low wing, si
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Mochizuki, Saya, and Gouji Yamada. "Aerodynamic characteristics and flow field of delta wings with the canard." MATEC Web of Conferences 145 (2018): 03010. http://dx.doi.org/10.1051/matecconf/201814503010.

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Now, many kinds of explorations for outer planets have been proposed around the world. Among them Mars attracts much attention for future exploration. Orbiters and landers have been used for Mars exploration. Recently as a new exploration method, the usage of an airplane has been seriously considered and there are some development projects for Mars airplane. However, the airplane flying on the Earth atmosphere cannot fly on the Mars atmosphere, because atmospheric conditions are much different each other. Therefore, we focused on the usage of the airplane with unfolding wings for Mars explorat
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de Mattos, Bento Silva, Paulo Jiniche Komatsu, and Jesuíno Takachi Tomita. "Optimal wingtip device design for transport airplane." Aircraft Engineering and Aerospace Technology 90, no. 5 (2018): 743–63. http://dx.doi.org/10.1108/aeat-07-2015-0183.

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Purpose The present work aims to analyze the feasibility of wingtip device incorporation into transport airplane configurations considering many aspects such as performance, cost and environmental impact. A design framework encompassing optimization for wing-body configurations with and without winglets is described and application examples are presented and discussed. Design/methodology/approach modeFrontier, an object-oriented optimization design framework, was used to perform optimization tasks of configurations with wingtip devices. A full potential code with viscous effects correction was
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Wang, Kang, Yuan Xue, Hongfeng Tian, Miaosen Wang, and Xiaolong Wang. "The Impact of Icing on the Airfoil on the Lift-Drag Characteristics and Maneuverability Characteristics." Mathematical Problems in Engineering 2021 (June 12, 2021): 1–16. http://dx.doi.org/10.1155/2021/5568740.

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Icing has now become an important factor endangering flight safety. This paper takes the icing data of the NACA 23012 airfoil as an example, establishes an icing influence model for real-time simulation based on icing time and aircraft angle of attack, and analyzes the influence of different icing geometry on aircraft characteristics. The two-dimensional interpolation method is used to improve the model of the aircraft’s stall area, which is mainly divided into the correction of the lift-drag coefficient linear area and the stall area and the correction of the aircraft stability derivative and
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Bruce Ralphin Rose, J., and Gr Jinu. "Gust Induced Aerodynamic Force Prediction on a Transport Wing Using Quasi-Steady Approximation." International Journal of Computational Methods 12, no. 06 (2015): 1550034. http://dx.doi.org/10.1142/s0219876215500346.

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The atmospheric wind turbulence over a specified time period has a strong influence on the airplane performance characteristics. Forecasting of this unsteady aerodynamic phenomenon is complex one for designing the control systems to ensure the structural safety. A novel approach is developed to assess the influence of a gust structure on the aerodynamic coefficients of an airplane. The load factor enhancement because of the discrete gust is also quantified to ensure the safety margin. The Kussner’s function is used to determine the time varying increment of gust-dependent lift produced on an a
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Донець, Олександр Дмитрович, та Володимир Олександрович Кудрявцев. "ОСОБЛИВОСТІ ЗАБЕЗПЕЧЕННЯ АЕРОДИНАМІЧНИХ ХАРАКТЕРИСТИК РЕГІОНАЛЬНОГО ПАСАЖИРСЬКОГО ЛІТАКА". Open Information and Computer Integrated Technologies, № 83 (23 травня 2019): 106–33. http://dx.doi.org/10.32620/oikit.2019.83.08.

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Principal results of the computational and research work performed during development of a regional passenger aircraft to ensure its aerodynamic characteristics are given. When creating the An-148-100/An-158 family of aircraft, such level of the aircraft aerodynamic perfection was achieved, which ensured fulfillment of the specified requirements for their flight performance – maximum speed, cruising flight altitude and flight range with different payloads. The developed aerodynamic configuration made it possible to create a family of regional passenger high-wing planes with a flight speed of u
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van Dam, C. P. "The aerodynamic design of multi-element high-lift systems for transport airplanes." Progress in Aerospace Sciences 38, no. 2 (2002): 101–44. http://dx.doi.org/10.1016/s0376-0421(02)00002-7.

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Dissertations / Theses on the topic "Lift (Aerodynamics) Airplanes"

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Robinson, Matthew J. "Simultaneous lift, moment and thrust measurement on a scramjet in hypervelocity flow /." [St. Lucia, Qld.], 2003. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe17611.pdf.

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Sathaye, Sagar Sanjeev. "Lift distributions on low aspect ratio wings at low Reynolds numbers." Link to electronic thesis, 2004. http://www.wpi.edu/Pubs/ETD/Available/etd-0427104-091112.

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Thesis (M.S.)--Worcester Polytechnic Institute.<br>Keywords: Low Reynolds Number; Micro Air Vehicle; Low Aspect Ratio; Spanwise pressure measurements; Spanwise Lift Distributions. Includes bibliographical references (p. 84-85).
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Naqvi, Messam Abbas. "Prediction of circulation control performance characteristics for super STOL & STOL applications." Available online, Georgia Institute of Technology, 2006, 2006. http://etd.gatech.edu/theses/available/etd-08172006-080403/.

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Thesis (Ph. D.)--Aerospace Engineering, Georgia Institute of Technology, 2007.<br>Dimitri N. Mavris, Committee Chair ; Lakshmi N. Sankar, Committee Member ; Daniel P. Schrage, Committee Member ; Robert J. Englar, Committee Member ; Robert C. Michelson, Committee Member.
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El, Akkad Adil. "Étude comparative des perturbations de la couche limite et de la portance, sur la plaque plane et sur modèle d'aile, en présence de fluides dégivrants /." Thèse, Chicoutimi : Université du Québec à Chicoutimi, 1993. http://theses.uqac.ca.

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Perron, Éric. "Modélisation du développement de la couche limité sur un film fluide /." Thèse, Chicoutimi : Université du Québec à Chicoutimi, 1993. http://theses.uqac.ca.

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Naqvi, Messam Abbas. "Prediction of Circulation Control Performance Characteristics for Super STOL and STOL Applications." Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/14123.

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The rapid air travel growth during the last three decades, has resulted in runway congestion at major airports. The current airports infrastructure will not be able to support the rapid growth trends expected in the next decade. Changes or upgrades in infrastructure alone would not be able to satisfy the growth requirements, and new airplane concepts such as the NASA proposed Super Short Takeo and Landing and Extremely Short Takeo and Landing (ESTOL) are being vigorously pursued. Aircraft noise pollution during Takeoff and Landing is another serious concern and efforts are aimed to reduce
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De, Grave Emiel. "Reverse Engineering of Passenger Jets - Classified Design Parameters." Master's thesis, Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2017. http://d-nb.info/1204457298.

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This thesis explains how the classified design parameters of existing passenger jets can be determined. The classified design parameters are; the maximum lift coefficient for landing and take-off, the maximum aerodynamic efficiency and the specific fuel consumption. The entire concept is based on the preliminary sizing of jet powered civil aeroplanes. This preliminary sizing is explained in detail because it is the foundation of the final result. The preliminary sizing is combined using reverse engineering which is not a strict method. Therefore, only the basics are explained. By applying reve
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Luke, Mark Elden. "Predicting Drag Polars For Micro Air Vehicles." Diss., CLICK HERE for online access, 2003. http://contentdm.lib.byu.edu/ETD/image/etd297.pdf.

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Books on the topic "Lift (Aerodynamics) Airplanes"

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Pittman, Jimmy L. Supersonic, nonlinear, attached-flow wing design for high lift with experimental validation. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Applin, Zachary T. Experimental and theoretical aerodynamic characteristics of a high-lift semispan wing model. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Rudolph, Peter K. C. High-lift systems on commercial subsonic airliners. National Aeronautics and Space Administration, Ames Research Center, 1996.

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Gilyard, Glenn B. Optimal pitch thrust-vector angle and benefits for all flight regimes. National Aeronautics and Space Administration, Dryden Flight Research Center, 2000.

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Michael, Mann, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Survey and analysis of research on supersonic drag-due-to-lift minimumization with recommendations for wing design. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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Michael, Mann, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Survey and analysis of research on supersonic drag-due-to-lift minimumization with recommendations for wing design. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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United States. National Aeronautics and Space Administration., ed. Numerical simulation of a powered-lift landing, tracking flow features using overset grids, and simulation of high lift devices on a fighter-lift-and-control wing. MCAT Institute, 1993.

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United States. National Aeronautics and Space Administration., ed. Numerical simulation of a powered-lift landing, tracking flow features using overset grids, and simulation of high lift devices on a fighter-lift-and-control wing. MCAT Institute, 1993.

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United States. National Aeronautics and Space Administration., ed. Experimental and computational investigation of lift-enhancing tabs on a multi-element airfoil. National Aeronautics and Space Administration, Ames Research Center, 1996.

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Center, Ames Research, ed. High-lift systems on commercial subsonic airliners. National Aeronautics and Space Administration, Ames Research Center, 1996.

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Book chapters on the topic "Lift (Aerodynamics) Airplanes"

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Wegener, Peter P. "Aerodynamic Lift." In What Makes Airplanes Fly? Springer US, 1991. http://dx.doi.org/10.1007/978-1-4684-0403-6_8.

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Wegener, Peter P. "Aerodynamic Lift." In What Makes Airplanes Fly? Springer New York, 1997. http://dx.doi.org/10.1007/978-1-4612-2254-5_8.

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Conference papers on the topic "Lift (Aerodynamics) Airplanes"

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Yadlin, Yoram, and Arvin Shmilovich. "Lift Enhancement for Upper Surface Blowing Airplanes." In 31st AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-2796.

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Khamedov, Ruslan, Ruslan Baitlessov, and Luis Rojas-Solórzano. "CFD Study of Effects of Boundary Layer Suction on Transonic SC(2)-0714 Airfoil Performance." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-70848.

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The complete understanding of the aerodynamics of wings and blades under transonic conditions represents a substantial challenge in the design of modern airplanes and turbomachinery. Transonic flow over airfoils may result in appearance of shock waves, which lead to increase in drag if not properly considered during the design stage. Therefore, it is a major challenge to design transonic airfoils such that potential appearance of shock waves is foreseen and negative drag effects are minimized. This paper presents the computational study of the SC(2)-0714 airfoil, focusing on its aerodynamics c
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Dimino, Ignazio, Salvatore Ameduri, and Antonio Concilio. "Preliminary Failure Analysis and Structural Design of a Morphing Winglet for Green Regional 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/smasis2018-8236.

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Aircraft wing design optimization typically requires the consideration of many competing factors accounting for both aerodynamics and structures. To address this, research on morphing aircraft has shown its potential by providing large benefits on aircraft performance. In particular, by adapting wing lift distribution, morphing winglets are capable to improve aircraft aerodynamic efficiency in off-design conditions and reduce wing loads at critical flight points. For those reasons, it is expected that these devices will be applied to the aircraft of the very next generation. In the study herei
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Staelens, Yann, Ron Blackwelder, and Mark Page. "Study of Belly-Flaps to Enhance Lift- and Pitching Moment Coefficient of a BWB-Airplane." In 25th AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-4176.

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Beck, B. Terry. "A Modular Wing-Tail Airplane Configuration for the Educational Wind Tunnel Laboratory." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-60418.

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An innovative modular airplane configuration has been developed for use in small-scale educational wind tunnels. The “airplane” consists of an interchangeable wing and horizontal tail configuration that mounts on a conventional wind tunnel electronic balance (“sting”) to facilitate measurements of normal force, axial force and longitudinal pitching moment. From these basic parameters, the total lift, total drag, and resultant airplane pitching moment can be deduced, along with the location of the aerodynamic center of the total airplane. Using known wing planform and airfoil shapes facilitates
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Alsulami, Anwar, Muhammad Akbar, and Woong Yeol Joe. "A Comparative Study: Aerodynamics of Morphed Airfoils Using CFD Techniques and Analytical Tools." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-72269.

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This paper presents an aerodynamics study of wing morphing by creating a Computational Fluid Dynamics (CFD) model using ANSYS FLUENT. First, known National Advisory Committee for Aeronautics (NACA) 2410 and 8410 profiles of airfoils are modeled. Models are run using prescribed initial and boundary conditions to simulate the morphed wing and flow around it. The Shear Stress Transport (SST) k–ω turbulence model is used to obtain an accurate comparison with the analytical results. Once satisfied with validation, variable cambers between NACA 2410 and 8410 are used in two ends of a wing to mimic a
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Kojima, Ryoji, Donghi Lee, Tomoaki Tatsukawa, Taku Nonomura, Akira Oyama, and Kozo Fujii. "Three-Dimensional Wing Design Towards the Future Mars Airplane." In ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajk2011-15013.

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The effects of aspect ratio and Reynolds number on aerodynamic characteristics of three-dimensional rectangular wing at low Reynolds number of 103 to 105, are investigated with Reynolds-averaged Navier-Stokes solver with the Baldwin-Lomax model. Present results show that lift coefficient decreases drastically at lower aspect ratio than 4. Besides, the much larger viscous drag coefficient is obtained at the lower Reynolds number, especially lower than 104. In order to focus on designing practical wings, the particular cases under the condition of fixed wing-surface area and fixed main stream ve
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Rea, Francesco, Francesco Amoroso, Rosario Pecora, and Markus Kintscher. "Design of an Adaptive Twist Trailing Edge for Large Commercial Aircraft Applications." In ASME 2018 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/smasis2018-7939.

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Researchers and engineers design modern aircraft wings to reach high levels of efficiency with the main outcome of weight saving and airplane lift-to-drag ratio increasing. Future commercial aircraft need to be mission-adaptive to improve their operational efficiency. Twistable trailing edge could be used to improve aircraft performances during climb and off-design cruise conditions in response to variations in speed, altitude, air temperature, and other flight parameters. Indeed, “continuous” span-wise twist of the wing trailing edge could provide significant reduction of the wing root bendin
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Hayashi, Ryosuke, Masaya Suzuki, and Makoto Yamamoto. "Numerical Investigation on Aerodynamic Performance of Twisted Blade for Human Powered Helicopter." In ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting collocated with 8th International Conference on Nanochannels, Microchannels, and Minichannels. ASMEDC, 2010. http://dx.doi.org/10.1115/fedsm-icnmm2010-30458.

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It is a dream for the human to freely fly in the sky by his/her own power. A human powered airplane has been developed and now we can fly for more than 100 km, while nobody has arrived at the height more than 1 m by a human powered helicopter. Therefore, the realization of a human powered helicopter will be a next dream of the human. The weight reduction is one of the most critical problems to realize a human powered helicopter. However, blades made of light materials are twisted and bent during hover. In this work, we perform three-dimensional simulation considering with fluid-structure inter
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Obeid, Sohaib, Ratneshwar Jha, and Goodarz Ahmadi. "Closed-Loop Feedback Control of Flow Over a Flapped Airfoil at High Angles of Attack Using Identified NARMAX Model." In ASME 2012 Fluids Engineering Division Summer Meeting collocated with the ASME 2012 Heat Transfer Summer Conference and the ASME 2012 10th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/fedsm2012-72350.

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This study investigates closed-loop feedback control system design aimed at reduction of turbulent flow separation over a NACA 0015 airfoil having 30% integral type trailing edge flap and equipped with leading-edge and trailing edge synthetic jet actuators (SJAs). The multiple-input single-output controller employs system identification techniques based on Nonlinear Auto Regressive Moving Average with eXogenous inputs (NARMAX) method to model nonlinear dynamics of the flow. RANS FLUENT simulations for 2-D airfoil are used besides an analytical modeling for the set of synthetic actuators. The r
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