Relevant bibliographies by topics / Trailing edge flaps

Contents

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

Academic literature on the topic 'Trailing edge flaps'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Trailing edge flaps"

1

Dalli, Uğbreve;ur, and Şcedilefaatdin Yüksel. "Identification of Flap Motion Parameters for Vibration Reduction in Helicopter Rotors with Multiple Active Trailing Edge Flaps." Shock and Vibration 18, no. 5 (2011): 727–45. http://dx.doi.org/10.1155/2011/675791.

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An active control method utilizing the multiple trailing edge flap configuration for rotorcraft vibration suppression and blade loads control is presented. A comprehensive model for rotor blade with active trailing edge flaps is used to calculate the vibration characteristics, natural frequencies and mode shapes of any complex composite helicopter rotor blade. A computer program is developed to calculate the system response, rotor blade root forces and moments under aerodynamic forcing conditions. Rotor blade system response is calculated using the proposed solution method and the developed program depending on any structural and aerodynamic properties of rotor blades, structural properties of trailing edge flaps and properties of trailing edge flap actuator inputs. Rotor blade loads are determined first on a nominal rotor blade without multiple active trailing edge flaps and then the effects of the active flap motions on the existing rotor blade loads are investigated. Multiple active trailing edge flaps are controlled by using open loop controllers to identify the effects of the actuator signal output properties such as frequency, amplitude and phase on the system response. Effects of using multiple trailing edge flaps on controlling rotor blade vibrations are investigated and some design criteria are determined for the design of trailing edge flap controller that will provide actuator signal outputs to minimize the rotor blade root loads. It is calculated that using the developed active trailing edge rotor blade model, helicopter rotor blade vibrations can be reduced up to 36% of the nominal rotor blade vibrations.
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Jia, Ya Lei, Zhong He Han, Fu You Li, Ya Kai Bai, and Ji Xuan Wang. "Influence of Flap Deflection Angle on Wind Turbine Airfoil with Trailing Edge Flaps." Advanced Materials Research 977 (June 2014): 222–27. http://dx.doi.org/10.4028/www.scientific.net/amr.977.222.

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To improve the ability of capturing the wind energy of wind turbine and shorten the design period is of great importance to designing wind turbine blade. The article established S809 airfoil model with trailing edge flaps, The gap of the frontal subject and trailing edge flap adopt uniform gap structure, this structure will reduce the influence of the gap on aerodynamic characteristics.Using the k-ω Two equation turbulence model , the article calculated aerodynamic performance of S809 with 10% chord length trailing edge flaps under different deflecting angles. Results show that gap between the main body and trailing edge flap has little effect on airfoil aerodynamic performance, however, the deflection Angle of Trailing edge flap have great affect on airfoil aerodynamic performance, when deflection Angle of trailing edge flap is 14 ° degrees ,the lift-to-drag ratio is the largest.
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Moriarty, J. A., and E. O. Tuck. "Thin aerofoils with high-incidence flaps or blunt trailing edges." Aeronautical Journal 93, no. 923 (1989): 93–99. http://dx.doi.org/10.1017/s0001924000016857.

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SummaryThe method of matched asymptotic expansions is used to calculate the lift for a class of thin aerofoils with highincidence flaps or blunt trailing edges. The analysis is based on smallness of the ratio between the flap length (or trailingedge thickness) and the chord of the main foil. Results are compared with exact solutions for bent plates and for triangular and quadrilateral bodies. A procedure for extension to general trailing-edge configurations, including detached flaps, is outlined.
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Pan, Lin, Ze Zhu, Zhaoyang Shi, and Leichong Wang. "Modeling and Investigation of Blade Trailing Edge of Vertical Axis Offshore Wind Turbine." Sustainability 13, no. 19 (2021): 10905. http://dx.doi.org/10.3390/su131910905.

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In this study, the structure of the trailing edge of the vertical axis offshore wind turbine blade is modified. First, according to the method of parameterization, the offshore wind turbine model is established, and a series of characteristics of the offshore wind turbine are obtained. Second, we add flaps with different lengths to the trailing edge of NACA0021 airfoil to obtain different dynamic characteristics. The angle of the additional trailing edge flaps is modified. Finally, a simulation model for the modified airfoil of the vertical axis offshore wind turbine is reestablished, and the variable characteristics of the performance is studied. Through the optimization and analysis of the blade structure, this study has obtained the best parameters of the length and angle of the offshore wind turbine blade trailing edge flap. The optimization of the blade structure changes the flow field around the blade, which significantly improves the maximum wind energy capture rate and self-starting ability of the vertical axis offshore wind turbine.
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Richter, K., and H. Rosemann. "Experimental investigation of trailing-edge devices at transonic speeds." Aeronautical Journal 106, no. 1058 (2002): 185–93. http://dx.doi.org/10.1017/s0001924000012987.

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AbstractThe influence of trailing-edge devices such as Gurney flaps and divergent trailing edges of different height on the aerodynamic performance of an aerofoil at transonic speeds has been investigated experimentally. The investigation has been carried out in the Transonic Wind Tunnel Göttingen (TWG) using the two-dimensional aerofoil model VC-Opt at freestream Mach numbers of M ε [0.755, 0.775, 0.790] and a Reynolds number of Re = 5.0 x 106.The results have shown that the trailing-edge devices increase the circulation of the aerofoil leading to a lift enhancement and pitching-moment decrease as well as an increase in minimum drag compared to the baseline configuration. The maximum lift-to-drag ratio is considerably improved and the onset of trailing-edge flow separation is shifted to higher lift. Besides the increased rear-loading, a downstream displacement of the shock provides the main lift enhancement in transonic flow.The simple Gurney flap provides the largest additional circulation of all geometries tested. The smoother turning of the flow due to the additional ramp of the divergent trailing edge leads to a smaller increase of circulation. Slightly less lift but considerably less viscous (pressure) drag is generated enhancing the maximum lift-to-drag ratio compared to the Gurney flap. The negative affect of the Gurney flap on the pitching moment is also reduced.For the high divergent trailing edges, different ramp slopes have a significant influence on the aerodynamic performance whereas at low device heights the influence is considerably diminished.The results show that the divergent trailing edge proves to be the better trailing-edge device at transonic speeds. The application as an element for an adaptive wing is generally possible.
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Saxena, Anand, and Inderjit Chopra. "Wind Tunnel Testing of a Swashplateless Rotor with Compact Brushless Motor Actuated Flaps for Primary Control." Journal of the American Helicopter Society 65, no. 1 (2020): 1–6. http://dx.doi.org/10.4050/jahs.65.012010.

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A swashplateless rotor trim using brushless DC motor actuated trailing edge flaps was achieved in the Glenn L. Martin wind tunnel. A 6-ft-diameter, four-bladed articulated rotor with motor–flap system integrated into the NACA 0012 airfoil section was fabricated. A Maxon EC-10 brushless DC motor as an on-blade actuator and a lightweight mechanism were incorporated to actuate the trailing edge flap. The rotor torsion frequency was lowered to 2/rev using soft pitch links, allowing the blade pitch response to a trailing edge flap input. A closed-loop controller was employed to ensure trailing edge flap operation at desired amplitude with correct phase difference and in sync with the rotor azimuth. A trim methodology was implemented, and wind tunnel trim was achieved at 900 and 1200 RPM for a number of advance ratios. Results show that the brushless DC motors can provide sufficient primary control authority and have structural strength to withstand centrifugal loads, while fitting within airfoil profile and incurring minimal weight penalty.
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Brown, L., and A. Filippone. "Aerofoil at low speeds with Gurney flaps." Aeronautical Journal 107, no. 1075 (2003): 539–46. http://dx.doi.org/10.1017/s0001924000013427.

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This paper reviews the research on Gurney flaps and related high lift trailing edge devices. It investigates aerofoil performances at Reynolds numbers Re ≅ 105 and below, both with the clean configuration and various Gurney flap sizes. The device height is optimised, and a semi-empirical formula linking flap height to free stream speed and aerofoil chord is proposed. The analysis shows that the optimal size of the device is always below the boundary-layer thickness at the trailing edge. Discussion of results includes analysis of hysteresis loops occurring in the L/D performances. These are mostly due to large changes in drag and small changes in lift, which occur when the aerofoil is restored to the reference angle of attack.
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Lendraitis, Martynas. "Investigation of performance gains on a sailplane with morphing wing trailing edge." Mechanics 25, no. 4 (2019): 299–303. http://dx.doi.org/10.5755/j01.mech.25.4.22325.

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Increasing the performance of a modern sailplane is challenging. Most of the known valid approaches have already been applied in practice. Morphing technology, which could allow to adapt to various flight stages is yet to be applied. An investigation of possible flight performance benefits of such technology is carried out here. Using a genetic algorithm, a morphing trailing edge flap for airfoil HQ-17 is formed for -4° and +12° flap deflections. The performance is evaluated and compared with a regular flap, which shows that for the HQ-17 airfoil, drag could be reduced by up to 36% in comparison with regular flap. To show the advantage of morphing flaps, a hypothetical sailplane wing is modeled and evaluated with morphing and conventional flaps using non-linear LLT method. Results show that incorporation of a morphing flap could extend the flight envelope and increase the L/D ratio by 2-5% trough the full flight speed range.
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Shen, Jinwei, and Inderjit Chopra. "Swashplateless Helicopter Rotor with Trailing-Edge Flaps." Journal of Aircraft 41, no. 2 (2004): 208–14. http://dx.doi.org/10.2514/1.9279.

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LIM, IN-GYU, and IN LEE. "AEROELASTIC ANALYSIS OF BEARINGLESS ROTOR SYSTEMS WITH TRAILING EDGE FLAPS." Modern Physics Letters B 23, no. 03 (2009): 461–64. http://dx.doi.org/10.1142/s0217984909018655.

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An aeroelastic analysis of bearingless rotor systems with trailing edge flaps was conducted using large deflection-type beam theory for forward flight conditions with a focus on reducing vibration while minimizing control effort. The aerodynamic forces of the rotor blade were calculated using two-dimensional quasi-steady strip theory. For the analysis of forward flight, the nonlinear periodic blade steady response was obtained by integrating the full finite element equation in time through a coupled trim procedure with a vehicle trim. The objective function, which includes vibratory hub loads and active flap control inputs, was minimized by an optimal control process. Numerical simulations were performed for the steady-state forward flight of various advance ratios. Numerical results of the steady blade and flap deflections as well as the vibratory hub loads were also presented for various advance ratios and were compared with previously published analysis results obtained from modal analyses based on a moderate deflection-type beam theory.
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Dissertations / Theses on the topic "Trailing edge flaps"

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Frederick, Mark. "Load reduction using rapidly deployed trailing-edge flaps." Thesis, Imperial College London, 2009. http://hdl.handle.net/10044/1/4647.

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This thesis details investigations into the aerodynamic properties of a small, rapidlyactuated, actively controlled trailing-edge ap and the potential of such a device to alleviate the unsteady loading experienced by wind turbine blades due to atmospheric turbulence and the atmospheric boundary layer, although such a device would have potential applications in other elds such as rotorcraft. The main goals of this work were to investigate whether aerodynamic loadings could in fact be alleviated by the use of a small trailing-edge ap using only measurements of the unsteady lift on the wing as a control input and to assess such a device's capacity to reject atmospheric disturbances with both numerical and experimental work, carried out in the Aeronautics Department at Imperial College London. The numerical work covered in the thesis comprises the results of linear and nonlinear aerodynamic and control simulations (e.g. PID, LQG controllers) and the results of computational uid dynamics (CFD) simulations using the commercial package FLUENT. The thesis also lays out the results obtained from testing an experimental prototype in the Hydrodynamics Laboratory in the Aeronautics Department. This prototype successfully rejected intentionally introduced ow disturbances from the vortex street of a square block upstream of the wing and the application of control provided a very signi cant reduction in the unsteady loading experienced by the wing. The ndings show the potential of this method of load control for the rejection of unsteady aerodynamic loading by the sole use of measurements of the wing loading and this has been demonstrated both theoretically and experimentally. The work is closed with a conclusion and suggestions for future research proposals.
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Yu, Jie. "Novel swing arm mechanism design for trailing edge flaps on commercial airliner." Thesis, Cranfield University, 2008. http://dspace.lib.cranfield.ac.uk/handle/1826/9586.

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This thesis will describe the works had been done by the author in the Flying Crane aircraft group design project and the new design of a novel swing arm mechanism which can be applied in the trailing edge high lift devices for this aircraft concept. Flying Crane aircraft is a new generation commercial airliner concept as the result of group design project conducted by China Aviation Industry Corporation I (AVIC I) and Cranfield University. At the end of the group design project, parameters such as take-off and landing distance, trailing edge flap type and deflection in take-off and landing configuration of the Flying Crane concept have been determined. These parameters are design input of the novel trailing edge high lift device mechanism for this aircraft concept. The idea of this innovative mechanism comes from the research achievement of a previous MSc student, Thomas Baxter, which applied swing arm mechanism into a passenger aircraft's leading edge slat. This thesis applied this idea to trailing edge flap and modeled the mechanism on CATIA software to yield a kinematic simulation for the purpose of check motion trail and force transfer in this mechanism. Relevant works such as actuation, mass and stress analysis are also involved. As the result of this research project, it was found that swing arm mechanism trends to require relatively small fairings for supports and attachments due to its high stowed space utilizing efficiency. Initial mass estimation carried out in this thesis also indicates that the new design takes advantage in terms of weight comparing with traditional trailing edge flap mechanisms. Thus. swing arm mechanism is supposed to show great competitive potential for commercial airliner's trailing edge flaps after further analysis has been done in the detail design phase.
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Couch, Mark A. "A three-dimensional flutter theory for rotor blades with trailing-edge flaps." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Jun%5fCouch%5FPhD.pdf.

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Thesis (Ph. D. in Aeronautical and Astronautical Engineering)--Naval Postgraduate School, June 2003.<br>Dissertation supervisor and advisor: E. Roberts Wood. Includes bibliographical references (p. 205-210). Also available online.
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Gagliardi, Adriano. "CFD analysis and design of a low-twist, hovering rotor equipped with trailing-edge flaps." Thesis, Connect to e-thesis, 2008. http://theses.gla.ac.uk/350/.

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Thesis (Ph.D.) - University of Glasgow, 2007.<br>Ph.D. thesis submitted to the Department of Aerospace Engineering, Faculty of Engineering, University of Glasgow, 2007. Includes bibliographical references. Print version also available.
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Schwarz, Eva [Verfasser]. "CFD-based studies of active wind turbine load control by means of trailing edge flaps / Eva Schwarz." München : Verlag Dr. Hut, 2021. http://d-nb.info/1238423051/34.

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Li, Wei-En. "Enhancement of roll maneuverability using post-reversal design." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/29602.

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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2009.<br>Committee Chair: Hodges, Dewey; Committee Member: Bauchau, Olivier; Committee Member: Goldsman, David; Committee Member: Prasad, J.V.R.; Committee Member: Smith, Marilyn. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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Schoensleben, Sven. "Integrated trailing edge flap track mechanism for commercial aircraft." Zürich : ETH, Eidgenössische Technische Hochschule Zürich, Center of Structure Technologies, 2006. http://e-collection.ethbib.ethz.ch/show?type=dipl&nr=228.

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Martins, Pires Rui Miguel. "Design methodology for wing trailing edge device mechanisms." Thesis, Cranfield University, 2007. http://hdl.handle.net/1826/3393.

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Over the last few decades the design of high lift devices has become a very important part of the total aircraft design process. Reviews of the design process are performed on a regular basis, with the intent to improve and optimize the design process. This thesis describes a new and innovative methodology for the design and evaluation of mechanisms for Trailing Edge High-Lift devices. The initial research reviewed existing High-Lift device design methodologies and current flap systems used on existing commercial transport aircraft. This revealed the need for a design methodology that could improve the design process of High-Lift devices, moving away from the conventional "trial and error" design approach, and cover a wider range of design attributes. This new methodology includes the use of the innovative design tool called SYNAMEC. This is a state-of-the-art engineering design tool for the synthesis and optimizations of aeronautical mechanisms. The new multidisciplinary design methodology also looks into issues not usually associated with the initial stages of the design process, such as Maintainability, Reliability, Weight and Cost. The availability of the SYNAMEC design tool and its ability to perform Synthesis and Optimization of mechanisms led to it being used as an important module in the development of the new design methodology. The SYNAMEC tool allows designers to assess more mechanisms in a given time than the traditional design methodologies. A validation of the new methodology was performed and showed that creditable results were achieved. A case study was performed on the ATRA - Advance Transport Regional Aircraft, a Cranfield University design project, to apply the design methodology and select from within a group of viable solutions the most suitable type of mechanism for the Variable Camber Wing concept initially defined for the aircraft. The results show that the most appropriate mechanism type for the ATRA Variable Camber Wing is the Link /Track Mechanism. It also demonstrated how a wide range of design attributes can now be considered at a much earlier stage of the design.
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Adair, Desmond. "Turbulent flow in the vicinity of the trailing-edge of an aerofoil flap." Thesis, Imperial College London, 1986. http://hdl.handle.net/10044/1/37915.

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Herdic, Scott Lucas. "Developement of Piezo-Hydraulic Actuation Systems Technology for use on a Helicopter Trailing Edge Flap." Thesis, Georgia Institute of Technology, 2005. http://hdl.handle.net/1853/7556.

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The purpose of this study was to create a proof-of-concept piezoelectric actuator system capable of meeting the performance requirements necessary for actuation of a trailing edge flap for a helicopter main rotor blade. Due to extremely small displacements produced by piezoelectric actuators, their output is amplified several times in order to produce the required displacement for this device. The amplification is accomplished in two stages. The first stage, mechanical amplification, uses differential length lever arms to increase the piezoelectric actuator output. The second stage, hydraulic amplification, is coupled to the first stage and uses differential area pistons to further amplify the output of the mechanical amplifier. The actuation systems force and displacement output is characterized based on frequency.
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Books on the topic "Trailing edge flaps"

1

Hassan, A. A. Blade-mounted trailing edge flap control for BVI noise reduction. Langley Research Center, 1992.

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2

Center, Langley Research, ed. Implementation of a trailing-edge flap analysis model in the NASA Langley CAMRAD.MOD1/HIRES program. National Aeronautics and Space Administration, Langley Research Center, 1999.

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Center, Langley Research, ed. Implementation of a trailing-edge flap analysis model in the NASA Langley CAMRAD.MOD1/HIRES program. National Aeronautics and Space Administration, Langley Research Center, 1999.

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W, Paulson John, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., eds. Low-speed aerodynamic characteristics of a wing-canard configuration with underwing spanwise blowing on the trailing-edge flap system. National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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W, Paulson John, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., eds. Low-speed aerodynamic characteristics of a wing-canard configuration with underwing spanwise blowing on the trailing-edge flap system. National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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Banks, Daniel W. Low-speed aerodynamic characteristics of a wing-canard configuration with underwing spanwise blowing on the trailing-edge flap system. Langley Research Center, 1987.

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Applin, Zachary T. Pressure distributions from subsonic tests of an advanced laminar-flow-control wing with leading- and trailing-edge flaps. National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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Applin, Zachary T. Pressure distributions from subsonic tests of an advanced laminar-flow-control wing with leading- and trailing-edge flaps. National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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Applin, Zachary T. Pressure distributions from subsonic tests of an advanced laminar-flow-control wing with leading- and trailing-edge flaps. National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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10

Gloria, Hernandez, and Langley Research Center, eds. Effect of leading- and trailing-edge flaps on clipped delta wings with and without wing camber at supersonic speeds. National Aeronautics and Space Administration, Langley Research Center, 1994.

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Book chapters on the topic "Trailing edge flaps"

1

Leble, Vladimir, and George N. Barakos. "Trailing and Leading Edge Flaps for Load Alleviation and Structure Control." In MARE-WINT. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-39095-6_7.

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Jost, Eva, Mário Firnhaber Beckers, Thorsten Lutz, and Ewald Krämer. "CFD Study of Trailing Edge Flaps for Load Control on Wind Turbines." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-64519-3_66.

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Kizhakke Kodakkattu, Saijal. "Design Optimization of Helicopter Rotor with Trailing-Edge Flaps Using Genetic Algorithm." In Advanced Engineering Optimization Through Intelligent Techniques. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-8196-6_48.

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Ghorawat, Prince, Keum W. Lee, Sahjendra N. Singh, and Grzegorz Chmaj. "Robust Finite-Time Control of an Uncertain Aeroelastic System Using Leading-and Trailing-Edge Flaps." In Advances in Intelligent Systems and Computing. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-48944-5_29.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Trailing-Edge Flap Placement." In Smart Helicopter Rotors. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_6.

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Bergami, Leonardo. "Adaptive Trailing Edge Flap Placement." In Research Topics in Wind Energy. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-07365-1_5.

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Bechert, D. W., R. Meyer, and W. Hage. "Drag Reduction on Gurney Flaps and Divergent Trailing Edges." In Aerodynamic Drag Reduction Technologies. Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-540-45359-8_25.

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Ha, Kwangtae. "Preliminary Study on Blade Trailing Edge Flap System Using Flexible Torsion Bar and Worm Drive." In EKC 2019 Conference Proceedings. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-8350-6_7.

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Marouf, A., N. SImiriotis, J. B. Tô, et al. "Numerical Study of Trailing-Edge Dynamics of a Two Element Airfoil-Flap with Morphing Flap at High Reynolds Number." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-55594-8_37.

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Haucke, Frank, Matthias Bauer, and Wolfgang Nitsche. "Combined Active Separation Control on the Leading Edge and on the Trailing Edge Flap of a Slatless High-Lift Configuration." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27279-5_19.

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Conference papers on the topic "Trailing edge flaps"

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Rennie, R., and Eric Jumper. "Gust alleviation using trailing-edge flaps." In 37th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-649.

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Milgram, Judah, and Inderjit Chopra. "Helicopter vibration reduction with trailing edge flaps." In 36th Structures, Structural Dynamics and Materials Conference. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-1227.

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Yerkes, Nicholas, and Norman Wereley. "Pneumatic Artificial Muscle Activation for Trailing Edge Flaps." In 46th AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-1418.

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Kurdila, Andrew J., Jing Li, Mark V. Fulton, and Glenn V. Webb. "Nonlinear control of PZT-actuated trailing edge flaps." In 1999 Symposium on Smart Structures and Materials, edited by Vasundara V. Varadan. SPIE, 1999. http://dx.doi.org/10.1117/12.350089.

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Calkins, F. T., and J. H. Mabe. "Flight Test of a Shape Memory Alloy Actuated Adaptive Trailing Edge Flap." In ASME 2016 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/smasis2016-9141.

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The Boeing Company has a goal of creating aircraft that are capable of continuous optimization for all flight conditions. Recent advances in SMA actuation and a detailed understanding of wing design were combined to design, build, and safely demonstrate small trailing edge flaps driven by SMA actuation. As part of a 2012 full-scale flight test program a lightweight and compact Shape Memory Alloy (SMA) rotary actuator was integrated into the hinge line of a small flap on the trailing edge of a commercial aircraft wing. This Adaptive Trailing Edge program was part of a Boeing and Federal Aviation Administration (FAA) collaboration. Aerodynamic studies of these small trailing edge flaps show that improved performance requires multiple flap configurations that vary with flight regime. Configurations include small angles of deployment for reduced fuel burn and emissions during high speed cruise and larger angles of deployment for increased lift and lower noise during takeoff and approach. SMA actuation is an ideal compact solution to position these small flaps and increase aircraft performance by simply and efficiently altering the wings aerodynamic characteristics for each flight segment. Closed loop control of the flap’s position, using the SMA actuator, was demonstrated at multiple flight conditions during flight tests. Results of the successful flight test on a 737–800 commercial airplane and the significantly improved performance benefits will be presented. This is the first flight test of an SMA rotary actuator system, which was matured from TRL 4 to TRL 7 during the program.
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Ahmed, Mohammed Rafiuddin, and Epeli Nabolaniwaqa. "Performance Improvement of a Wind Turbine Blade Designed for Low Wind Speeds With a Passive Trailing Edge Flap." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-88417.

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The flow characteristics and the lift and drag behavior of a newly designed thick trailing-edged airfoil that was provided with fixed trailing edge flaps (Gurney flaps) of 1% to 5% height right at the back of the airfoil were studied at different low Reynolds numbers (Re) and angles of attack for possible applications in wind turbines suitable for the wind speeds of 4–6 m/s that are common in the Pacific Island Countries. A thick trailing-edged blade section, AF300, that was designed and tested in a recent work for small horizontal axis wind turbines to improve the turbine’s startup and performance at low wind speeds was chosen for this study. Experiments were performed on the AF300 airfoil in a wind tunnel at different Re, flap heights and angles of attack. Pressure distributions were obtained across the surface of the airfoil and the lift and drag forces were measured for different cases. It was found that the flap considerably improves the suction on the upper surface of the airfoil resulting in a high lift coefficient. For some of the angles, in the case of 3 mm and 4 mm flaps, the peak Cp values on the suction surface were significantly higher compared to those without the flap. However, at angles of attack of 12° and above, this unusually high Cp on the upper surface close to the leading edge caused flow separation for some cases as the flow could not withstand the strong adverse pressure gradient. The CFX results matched most of the experimental results without flaps, except that the suction peak was lower numerically. The difference was higher for the case with flaps. It is clear from the results that trailing-edge flaps can be used to improve the performance of small wind turbines designed for low wind speeds.
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7

Kizhakke Kodakkattu, Saijal, Prabhakaran Nair, and M. L. Joy. "Robust Optimal Trailing-Edge Flaps for Helicopter Vibration Reduction for Various Flying Conditions." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-53150.

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This paper aims to find a robust optimal design for twin trailing-edge flap for helicopter vibration reduction for various flying conditions with minimum flap power requirement. The objective is to find the optimum length and locations of twin trailing-edge flaps to minimize hub vibration in the helicopter with minimum flap power requirement and to evaluate the robustness of these optimum at various flying conditions such as advance ratio and thrust to solidity ratio. Polynomial response surface metamodels is used to approximate the hub vibration and flap power objective functions for optimization. Firstly, a single objective optimization minimizing hub vibration alone is carried out without considering the flap power requirement. A multi-objective optimization minimizing vibration and flap power is also carried out to explore the possibility of a compromise design of trailing-edge flaps. This optimization finds the robust optimal length and locations of twin trailing-edge flaps with the objective of minimizing hub vibration for various flying conditions. Result shows that a flap length of 9 percentage of the rotor is the optimum giving 55 percentage reduction in hub vibration compared to the baseline values. The corresponding inboard and outboard flap positions are 0.61R and 0.87R respectively. The robustness of these design solution with flying conditions such as advance ratio and thrust to solidity ratio are also explored.
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8

Hunsaker, Douglas F., Jackson T. Reid, Bruno Moorthamers, and James J. Joo. "Geometry and Aerodynamic Performance of Parabolic Trailing-Edge Flaps." In 2018 AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-1278.

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9

Segawa, Hidehiro, and Ashok Gopalarathnam. "Optimum Flap Angles for Roll Control on Wings with Multiple Trailing-Edge Flaps." In 46th AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-319.

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10

Bhavsar, Kathan, and Jessica Kartha. "Comparative CFD Analysis of Different Angles of Trailing-Edge Fowler Wing Flaps." In 2023 AeroTech. SAE International, 2023. http://dx.doi.org/10.4271/2023-01-1023.

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&lt;div class="section abstract"&gt;&lt;div class="htmlview paragraph"&gt;This paper focuses on a case study to compare the performances of Fowler wing flaps that are used on the trailing edge of modern-day commercial airliners. The aim is to observe trends in coefficients of lift (C&lt;sub&gt;l&lt;/sub&gt;) and drag (C&lt;sub&gt;d&lt;/sub&gt;) with varying flap angles of release on a single-slotted Fowler flap and arrive at the most efficient flap configuration for flight. A series of two-dimensional analyses are carried out using computational fluid dynamics (CFD) to examine the flow separation and occurrence of stalls between the different angles of flap deflection. A two-equation, k-ω shear stress transport (SST) turbulence model is used as it helps in better prediction of flow separation and boundary layer studies. Since the study is carried out for such passenger carriers, the study focuses on the lower transonic ranges of Mach number 0.7-0.9 with a Reynolds number range of 400,000 to 500,000 considering a scaled-down model and upon taking inspiration from related literature. The flaps are analyzed at various angles of release (α) such as 0°, 15°, 25°and 50°, which are selected considering the angles that they are commonly deflected to during take-off and landing scenarios. A NACA0012 symmetrical airfoil is chosen with a fixed chord length for the wing and kept at 0° Angle of Attack (AoA) with subsequent trailing edge Fowler flaps employed for examination. A data-driven approach is followed for the investigation of characteristics represented by the different designs of the Fowler flap, thus typical lift curve plots (C&lt;sub&gt;l&lt;/sub&gt; vs α), drag plots (C&lt;sub&gt;d&lt;/sub&gt; vs α), and lift-to-drag ratio (C&lt;sub&gt;l&lt;/sub&gt;/C&lt;sub&gt;d&lt;/sub&gt;) plots (C&lt;sub&gt;l&lt;/sub&gt;/C&lt;sub&gt;d&lt;/sub&gt; vs α) graphs are presented to understand the comparative study. The results are discussed with respect to the data observed in the graphs and a viable conceptual configuration for the single-slotted Fowler flap is selected. This insight, research, and design have led to the development of the research paper and it is hoped that this comparative study can be used to conduct further research in the field of aeronautics.&lt;/div&gt;&lt;/div&gt;
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Reports on the topic "Trailing edge flaps"

1

Moore, Frank G., and Tom C. Hymer. A Semiempirical Method for Predicting Aerodynamics of Trailing Edge Flaps. Defense Technical Information Center, 2001. http://dx.doi.org/10.21236/ada390471.

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