Relevant bibliographies by topics / Aerodynamic load

Contents

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

Academic literature on the topic 'Aerodynamic load'

Author: Grafiati
Published: 4 June 2021
Last updated: 31 July 2024

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Journal articles on the topic "Aerodynamic load"

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Tomasz Lusiak, Andrej Novak, Martin Bugaj, and Radovan Madlenak. "Assessment of Impact of Aerodynamic Loads on the Stability and Control of the Gyrocopter Model." Communications - Scientific letters of the University of Zilina 22, no. 4 (October 1, 2020): 63–69. http://dx.doi.org/10.26552/com.c.2020.4.63-69.

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Aerodynamic modelling currently relates to development of mathematical models to describe the aerodynamic forces and moments acting on the aircraft. It is a challenging part of aerodynamics that defines a comprehensive approach to using traditional methods and modern techniques to obtain relevant data. The most complicated task for the aerodynamics and flight dynamics is definition, computation and quantification of the aerodynamic description of an object. This paper presents how to determine the aerodynamic load on a gyrocopter and defines the effect on its stability and control. The first step to solution is to develop simpler approximate aerodynamic model - a model that can be used in analysis of aerodynamic load and can represent the aerodynamic properties of the gyrocopter with an acceptable degree of accuracy. Control and stability are very important parts of aircraft characteristics and therefore those characteristics were analyzed in simulation. Finally, the aerodynamic data outputs are assessed in terms of impact of aerodynamic loads on stability and control of the gyrocopter model.
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Perez-Becker, Sebastian, Francesco Papi, Joseph Saverin, David Marten, Alessandro Bianchini, and Christian Oliver Paschereit. "Is the Blade Element Momentum theory overestimating wind turbine loads? – An aeroelastic comparison between OpenFAST's AeroDyn and QBlade's Lifting-Line Free Vortex Wake method." Wind Energy Science 5, no. 2 (June 15, 2020): 721–43. http://dx.doi.org/10.5194/wes-5-721-2020.

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Abstract. Load calculations play a key role in determining the design loads of different wind turbine components. To obtain the aerodynamic loads for these calculations, the industry relies heavily on the Blade Element Momentum (BEM) theory. BEM methods use several engineering correction models to capture the aerodynamic phenomena present in Design Load Cases (DLCs) with turbulent wind. Because of this, BEM methods can overestimate aerodynamic loads under challenging conditions when compared to higher-order aerodynamic methods – such as the Lifting-Line Free Vortex Wake (LLFVW) method – leading to unnecessarily high design loads and component costs. In this paper, we give a quantitative answer to the question of load overestimation of a particular BEM implementation by comparing the results of aeroelastic load calculations done with the BEM-based OpenFAST code and the QBlade code, which uses a particular implementation of the LLFVW method. We compare extreme and fatigue load predictions from both codes using sixty-six 10 min load simulations of the Danish Technical University (DTU) 10 MW Reference Wind Turbine according to the IEC 61400-1 power production DLC group. Results from both codes show differences in fatigue and extreme load estimations for the considered sensors of the turbine. LLFVW simulations predict 9 % lower lifetime damage equivalent loads (DELs) for the out-of-plane blade root and the tower base fore–aft bending moments compared to BEM simulations. The results also show that lifetime DELs for the yaw-bearing tilt and yaw moments are 3 % and 4 % lower when calculated with the LLFVW code. An ultimate state analysis shows that extreme loads of the blade root out-of-plane bending moment predicted by the LLFVW simulations are 3 % lower than the moments predicted by BEM simulations. For the maximum tower base fore–aft bending moment, the LLFVW simulations predict an increase of 2 %. Further analysis reveals that there are two main contributors to these load differences. The first is the different way both codes treat the effect of the nonuniform wind field on the local blade aerodynamics. The second is the higher average aerodynamic torque in the LLFVW simulations. It influences the transition between operating modes of the controller and changes the aeroelastic behavior of the turbine, thus affecting the loads.
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Tian, Xiao, Wenhui Yan, and Kun Zhang. "Numerical Calculation of 1P Aerodynamic Loads on Aviation Propellers." Journal of Physics: Conference Series 2747, no. 1 (May 1, 2024): 012043. http://dx.doi.org/10.1088/1742-6596/2747/1/012043.

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Abstract To accurately predict the 1P aerodynamic loads of aviation propellers, this paper established a mathematical model of aviation propeller 1P aerodynamic loads based on the coupling method of blade element theory and momentum theory. Correction methods such as the Prandtl tip correction method and the propeller root correction method were implemented to further improve calculation accuracy. A 1P aerodynamic load calculation procedure was developed based on the mathematical model by using the Matlab software. 1P aerodynamic loads of a three-blade propeller were predicted for three different angles including 3 °, 9 °, and 12°. The numerical calculation results show that the calculated aerodynamic characteristic parameters of individual propeller blades obtained based on the propeller 1P aerodynamic load mathematical model deviate less than 6% from the CFD simulation results, and regular periodic pulsations are observed. The numerical calculations in this paper show that the propeller 1P aerodynamic load calculation procedure developed based on this model can accurately predict the propeller 1P aerodynamic load, which can provide some reference for the study of aviation propeller aerodynamic characteristics.
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Cicolani, L. S., J. G. A. da Silva, E. P. N. Duque, and M. B. Tischler. "Unsteady aerodynamic model of a cargo container for slung-load simulation." Aeronautical Journal 108, no. 1085 (July 2004): 357–68. http://dx.doi.org/10.1017/s0001924000005170.

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Abstract The problem of simulation models capable of predicting the aerodynamic instability of helicopter slung-load cargo containers and bluff bodies is addressed. Instability for these loads is known to depend on unsteady frequency-dependent aerodynamics, but simulation models that include the unsteady aerodynamics do not currently exist. This paper presents a method for generating such models using computational fluid dynamics (CFD) to generate forced-oscillation aerodynamic data and frequency domain system identification techniques to generate a frequency response from the CFD data and to identify a transfer function fit to the frequency response. The method is independent of the responsible flow phenomenon and is expected to apply to bluff-bodies generally. Preliminary results are presented for the case of the 6- by 6- by 8-ft CONEX (container express) cargo container. The present work is based on two-dimensional (2D) aerodynamic data for the CONEX side force and yaw moment generated by a forced oscillation in which frequency is varied smoothly over the range of interest. A first-order rational polynomial transfer function is found adequate to fit the aerodynamics, and this is shown to provide a good match with flight test data for the yawing motion of the CONEX.
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Gennaretti, M., and C. Ponzi. "Finite-state aerodynamic modelling for gust load alleviation of wing–tail configurations." Aeronautical Journal 103, no. 1021 (March 1999): 147–58. http://dx.doi.org/10.1017/s0001924000064964.

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Abstract A finite-state aerodynamics methodology is proposed for the analysis of the forces generated by a gust. To illustrate and assess the methodology, gust-response and gust-alleviation applications are included. Finite-state aerodynamics denotes a technique to approximate aerodynamic loads so as to yield an aircraft model of the type ẋ = Ax + Bu (state-space formulation). In this paper, a finite-state formulation is proposed to include the presence of a gust. The aerodynamic loads to be approximated are evaluated here by using a frequency-domain boundary-element formulation; the flow is assumed to be irrotational except for a zero-thickness vortex layer (wake). The gust-alleviation application consists of determining a control law for reducing the response to a vertical gust disturbance, as measured by the centre of mass acceleration. Two optimal-control approaches are considered for the synthesis of the control law: one uses the classical linear-quadratic regulator (LQR), whereas the second includes the additional feed-forward of the gust velocity ahead of the aircraft. Deflections of ailerons and elevators are assumed to be the control variables. Numerical results deal with responses to both a deterministic ‘1 – cosine’ gust distribution and a stochastic von Kármán spectrum. They indicate that the finite-state aerodynamic model proposed is capable of approximating, with a high level of accuracy, both the aerodynamic loads induced by the aircraft kinematics variables and those induced by the control variables, over a wide frequency range.
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Ma, Kaichao, Changhong Tang, Jianye Zhang, Xiaofei Niu, and Qingzhi Fan. "Flight Load Design of Nacelle of Carrier-Based Propeller Transport Aircraft." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, no. 6 (December 2020): 1249–56. http://dx.doi.org/10.1051/jnwpu/20203861249.

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The carrier-based propeller transport aircraft has a compact layout, where the large nacelle in size and weight is sensitive to propeller slipstream, and thus calls for sophisticated flight load design studies, which are still insufficient considering domestic experience. In detail, the design methods on aerodynamic load, inertial load, gyrostatic moment, as well as studies on design criteria and maneuver simulation technology are shown for a reference aircraft. The design range applied to this nacelle's flight load is firstly determined by understanding and selecting the design criteria. The typical loadcases of the nacelle are derived from aircraft maneuver simulation. The data of pressure distribution under a series of propeller slipstream strengths is obtained by CFD method. The Design Loads and Design Loadcases of the nacelle are calculated and selected. The effects of the propeller slipstream are compared in an example of the increment on aerodynamic load in a maneuver. The results show that the Design Loads of the nacelle are obtained from the abrupt pitching maneuver under the maximum normal load factor (Nz), the yawing maneuver under the Design Dive Speed(VD), and the maximum propeller pull under the maximum landing weight; the transverse loads of the nacelle are dominated by the aerodynamic load, and the normal loads are dominated by the inertial load, in which the inertial force exceeds the aerodynamic force by 4 times under the extreme circumstances. In some manoeuvres or status, the total aerodynamic force of the whole nacelle is increased by above 90% due to propeller slipstream; the front part of the nacelle which is close to the propeller sees a much bigger increment.
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Liu, Mengjuan, Han Wu, Junqi Xu, Xiaohui Zeng, Bo Yin, and Zhanzhou Hao. "Research on sliding mode controller of the high-speed maglev train under aerodynamic load." Advances in Mechanical Engineering 14, no. 10 (October 2022): 168781322211278. http://dx.doi.org/10.1177/16878132221127857.

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The high-speed maglev train will be subjected to extremely obvious aerodynamic load and instantaneous aerodynamic impact during passing another train, which brings significant challenges to the train’s suspension stability and safe operation. It’s necessary to consider the influence of aerodynamic load and shock waves in the design of suspension control algorithms. Traditional proportion integration differentiation (PID) control cannot follow the change of vehicle parameters or external disturbance, which is easy to cause suspension fluctuation and instability. To improve the suspension stability and vibration suppression of the high-speed maglev train under aerodynamic load and impact, we design a siding mode controller introducing the primary suspension’s deformation to replace the aerodynamic load on the electromagnet. Furthermore, we establish the train’s dynamic simulation model with three vehicles and compare the designed controller and the PID controller for their performance in controlling the model suspension stability in the presence of the train operating in open air. Simulation results show that the sliding mode control (SMC) method proposed in this paper can effectively restrain the electromagnet fluctuation of the train under aerodynamic loads.
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Didenko, Anton, Vladislav Borisenko, and Jose Leoro. "Load distribution method in helicopter blade multibody dynamics system." E3S Web of Conferences 258 (2021): 09076. http://dx.doi.org/10.1051/e3sconf/202125809076.

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The paper focuses on the loads applied to the helicopter blade cross-sections in the multibody dynamics system. The main objective is to simplify the blade aerodynamics calculation and avoid time-consuming CFD methods. For this reason, the way of computing blade aerodynamics is proposed by using multibody dynamics methods with a linear-elastic blade model. As the primary tool for further research, the MCS Adams software package is selected. Splitting the main rotor blade into a finite number of sections, each having its own average value of installation and coning angles, simplifies the calculation. Afterward, expressions for the total flow velocity around the blade section and its angle of attack are obtained through vector operations. This provides a measure of aerodynamic forces acting on each section in its cross-sectional coordinate system. In conclusion, the article provides the formalized method of aerodynamic force distribution between blade sections in the multibody model as well as the correlation between the flow coordinate system and the blade chord coordinate system.
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Xie, Yonghui, Kun Lu, Le Liu, and Gongnan Xie. "Fluid-Thermal-Structural Coupled Analysis of a Radial Inflow Micro Gas Turbine Using Computational Fluid Dynamics and Computational Solid Mechanics." Mathematical Problems in Engineering 2014 (2014): 1–10. http://dx.doi.org/10.1155/2014/640560.

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A three-dimensional fluid-thermal-structural coupled analysis for a radial inflow micro gas turbine is conducted. First, a fluid-thermal coupled analysis of the flow and temperature fields of the nozzle passage and the blade passage is performed by using computational fluid dynamics (CFD). The flow and heat transfer characteristics of different sections are analyzed in detail. The thermal load and the aerodynamic load are then obtained from the temperature field and the pressure distribution. The stress distributions of the blade are finally studied by using computational solid mechanics (CSM) considering three cases of loads: thermal load, aerodynamics load combined with centrifugal load, and all the three types of loads. The detailed parameters of the flow, temperature, and the stress are obtained and analyzed. The numerical results obtained provide a useful knowledge base for further exploration of radial gas turbine design.
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Harinaldi Harinaldi and Farhan T Pratama. "Transient Analysis on the Crosswind Effect to the Aerodynamics of High-speed Train Travelled on the Bridge Between Two Tunnels at Jakarta -Bandung Track." CFD Letters 16, no. 10 (June 2, 2024): 64–80. http://dx.doi.org/10.37934/cfdl.16.10.6480.

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The rapid evolution of global transportation technology is exemplified by Indonesia's innovative high-speed train initiative, linking Jakarta and Bandung in an impressive 45 minutes. Operating at 350 km/h, the HST CR400AF underscores the importance of aerodynamics in high-speed rail systems. This study delves into the significant impact of crosswind on key aerodynamic factors (drag, lift, rolling moment) within the tunnel-bridge-tunnel configuration. Leveraging Computational Fluid Dynamics (CFD) through ANSYS FLUENT, the analysis explores crosswind variations at 0 m/s, 10 m/s, and 25 m/s. Results reveal a proportional increase in aerodynamic load with higher crosswind intensities: 1.67 times for drag, 58.8 times for lift, and 29.8 times for rolling moment. Notable observations include pronounced aerodynamic load fluctuations during the "OUT" process, with the head section bearing the greatest load, followed by the tail and middle sections. These findings contribute valuable insights to the global discourse on enhancing safety and efficiency in high-speed rail systems
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Dissertations / Theses on the topic "Aerodynamic load"

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Heene, Mario. "Aerodynamic Propeller Model for Load Analysis." Thesis, KTH, Matematik (Inst.), 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-103226.

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An aerodynamic propeller model, which can contribute to the prediction of structural loads experienced by aircraft in different flight maneuvers is presented.The model is based on Blade Element Momentum theory and is able to predict the unsymmetrical and frequency-dependent forces and moments induced by the propeller on the airplane structure at steady and unsteady inflow-conditions.In order to validate the model, a comparison with experimental results was performed and it can be seen that the model is in agreement with the experimental data providing that the aerodynamic data used for the calculations has good accuracy.
En modell har utvecklats för att beräkna aerodynamiska krafter som orsakas av propellern vid manöverflygning. Modellen använder sig av klassiska bladelementteorin för predikering av osymmetriska stationära krafter som uppstår vid snedanblåsning av propellerskivan. Modellen kommer att användas inom ett forskningsprojekt om effektiv beräkning av aerodynamiska laster vid flygmanövrar och i vindbyar. En vidareutveckling av den klassiska metoden används för att ta fram instationära kraftbidrag i frekvensplanet i en form som är lämpligt för aeroelastiska stabilitetsanalys och beräkning av vindbylasterna.Jämförelser med omfattande experimentella resultat har genomförts för att validera modellen. Inom ramen för antaganden och noggrannheten i modellens indata kan modellens tillförlitighet bedömas som tillräckligt för ändamålet. Däremot visar sig att propellermodellen är -- som förväntat -- mindre lämpligt för att bedöma propellerlasterna utanför propellerns reguljära driftområdet.
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Gillam, David A. "Airloads on a finite wing in a time dependent incompressible freestream." Diss., Georgia Institute of Technology, 1994. http://hdl.handle.net/1853/12371.

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Saini, Manjinder. "Experimental and computational study of airfoil load alteration using oscillating fence actuator." Laramie, Wyo. : University of Wyoming, 2008. http://proquest.umi.com/pqdweb?did=1663059971&sid=3&Fmt=2&clientId=18949&RQT=309&VName=PQD.

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McNabb, Michael Lynn. "Development of a cycloidal propulsion computer model and comparison with experiment." Master's thesis, Mississippi State : Mississippi State University, 2001. http://library.msstate.edu/etd/show.asp?etd=etd-08032001-111940.

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Standingford, David William Fin. "Optimal lifting surfaces, including end plates, ground effect & thickness /." Title page, contents and abstract only, 1997. http://web4.library.adelaide.edu.au/theses/09PH/09phs785.pdf.

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Wilks, Brett Landon Burkhalter Johnny Evans. "Aerodynamics of wrap-around fins in supersonic flow." Auburn, Ala., 2005. http://repo.lib.auburn.edu/2005%20Fall/Thesis/WILKS_BRETT_54.pdf.

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Wacker, Thomas. "A preliminary study of configuration effects on the drag of a tractor-trailer combination." Thesis, University of British Columbia, 1985. http://hdl.handle.net/2429/25143.

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The effect of configuration changes and add-on devices on the drag reduction of a tractor-trailer is studied through wind tunnel tests using two 1/12-scale models. The configuration changes involve ground clearance, tractor-trailer gap, roof angle and back inclination while add-on devices include flow deflectors, skirts and gap seals. Moving surface boundary layer control as a means of drag reduction is also attempted. Both drag and pressure data are obtained to help identify local contributions. Results suggest that an optimum combination of configuration parameters can reduce drag up to 17% while the add-on devices resulted in a further decrease by a modest amount. The results with moving surface boundary layer control proved to be inconclusive.
Applied Science, Faculty of
Mechanical Engineering, Department of
Graduate
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Zink, Paul Scott. "A methodology for robust structural design with application to active aeroelastic wings." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12424.

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Liu, Haiying. "Interfacing comprehensive rotorcraft analysis with advanced aeromechanics and vortex wake models." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/22534.

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Thesis (Ph. D.)--Aerospace Engineering, Georgia Institute of Technology, 2008.
Committee Chair: Bauchau, Olivier; Committee Member: Armanios, Erian; Committee Member: Hodges, Dewey; Committee Member: Ruzzene, Massimo; Committee Member: Stallybrass, Michael.
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Page, Anthony Baker. "Piecewise-constant control strategies for use in minimum fuel aeroassisted orbital transfers." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-08042009-040438/.

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Books on the topic "Aerodynamic load"

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United States. National Aeronautics and Space Administration., ed. A characteristic method for calculating the generalized flat flutter aerodynamic forces. Washington, DC: National Aeronautics and Space Administration, 1988.

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Development, North Atlantic Treaty Organization Advisory Group for Aerospace Research and. Aircraft dynamic loads due to flow separation. Neuilly sur Seine, France: AGARD, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Aircraft dynamic loads due to flow separation. Neuilly-sur-Seine: AGARD, 1990.

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Pérez, Sergio Adrián. Sergio Adrián Pérez. Downsview, Ont: Institute for Aerospace Studies, University of Toronto, 1990.

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Moshasrov, V. Luminescent pressure sensors in aerodynamic experiments. Zhukovsky, Russia : Central Aerohydrodynamic Institute (TsAGI): CWA 22 Corporation, 1998.

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R, Burley James, Bare E. Ann, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Parametric study of afterbody/nozzle drag on twin two-dimensional convergent-divergent nozzles at mach numbers from 0.60 to 1.20. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Bjarke, Lisa J. A summary of the forebody high-angle-of-attack aerodynamics research on the F-18 and the X-29A aircraft. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1992.

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Wing, David J. Afterbody/nozzle pressure distributions of a twin-tail twin-enginer fighter with axisymmetric nozzles at Mach numbers from 0.6 to 1.2. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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Bjarke, Lisa J. A summary of the forebody high-angle-of-attack aerodynamics research on the F-18 and the X-29A aircraft. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1992.

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Lee, B. H. K. Forced oscillation of a two-dimensional airfoil with nonlinear aerodynamic loads. Ottawa: National Aeronautical Establishment, 1986.

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Book chapters on the topic "Aerodynamic load"

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Soper, David. "Aerodynamic Load Experiment Setup." In The Aerodynamics of a Container Freight Train, 135–57. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-33279-6_5.

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Soper, David. "Aerodynamic Load Experiment Processing Methodology." In The Aerodynamics of a Container Freight Train, 159–77. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-33279-6_6.

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Soper, David. "Aerodynamic Load Analysis, Results and Discussion." In The Aerodynamics of a Container Freight Train, 179–223. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-33279-6_7.

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Wiedemann, Martin. "Lightweight System Design with Integration of Passive Functions." In essentials, 27–33. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-44165-3_3.

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AbstractPassive functions are not used for load transfer alone, as in classic lightweight design, but fulfil other requirements for the overall product, such as minimising aerodynamic drag, providing electrical conductivity and thermal or acoustic insulation.
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Tan, Linlin. "Research on the Aerodynamic Failure Load for Civil Aircraft." In Lecture Notes in Electrical Engineering, 857–67. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2689-1_65.

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Feng, Xiao-lei, and Xi-wei Zhou. "Multi-condition Aerodynamic Load Simulation Study of an Airborne External Rotating Equipment." In Proceedings of the Eighth Asia International Symposium on Mechatronics, 1547–55. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-1309-9_149.

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Valikhani, Mohammad, Vahid Jahangiri, Hamed Ebrahimian, Sauro Liberatore, Babak Moaveni, and Eric Hines. "Aerodynamic Load Estimation in Wind Turbine Drivetrains Using a Bayesian Data Assimilation Approach." In Model Validation and Uncertainty Quantification, Volume 3, 67–71. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-37003-8_10.

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Li, Guandong, Qiulin Qu, and Peiqing Liu. "Experimental Studies on the Load Characteristics of Low-Speed Droplets Impinging onto Surface." In Lecture Notes in Mechanical Engineering, 937–46. Singapore: Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-1876-4_74.

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AbstractDroplet impingement on a wall is a fundamental scientific problem with wide engineering applications. When a droplet impacts the surface of an aircraft, it generates shock waves, airflow disturbances, and splashing phenomena. This not only has a negative impact on the aerodynamic performance and stability of the aircraft but also obstructs the field of view of optical sensors or causes distortion in optical devices. It can also damage the aircraft's structure, thus it’s vital to assess the droplet impact force for flight safety. However, droplets are often treated as rigid spheres for simplicity, but this does not reflect the real physical situation. In this paper, we utilized high-precision force sensors and high-speed imaging technology to experimentally investigate the impact dynamic of droplet impingement on a dry wall. The temporal evolution of force, the associated morphology changes and their relationship during collisions were analyzed systematically, we also elucidated the physical mechanisms underlying flow phenomenon. An unified and accurate mechanical model were established for droplet impingement, providing guidance for related engineering designs.
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Gao, Yuehua, Wenzhong Zhao, Yonghua Li, and Bingzhi Chen. "Optimum Structural Designs for an Equipment Cabin under High-Speed Train Considering Aerodynamic Load." In Proceedings of the 1st International Workshop on High-Speed and Intercity Railways, 199–204. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-27963-8_20.

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Al-Chalabi, Raghdah, Muhammad Ibrahim, and Ahmed Elshaer. "Computational Wind Load Evaluation and Aerodynamic Mitigation of Low-Rise Building with Complex Roof Geometry." In Lecture Notes in Civil Engineering, 247–60. Cham: Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-34027-7_16.

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Conference papers on the topic "Aerodynamic load"

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Al-Battal, Nader, David Cleaver, and Ismet Gursul. "Aerodynamic Load Control through Blowing." In 54th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1820.

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Qiu, Ju, and Qin Sun. "Research of aerodynamic load of horizontal tail." In 2009 4th IEEE Conference on Industrial Electronics and Applications. IEEE, 2009. http://dx.doi.org/10.1109/iciea.2009.5138445.

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Mangalam, Arun, Siva Mangalam, and Peter Flick. "Unsteady Aerodynamic Observables for Gust Load Alleviation." In 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
16th AIAA/ASME/AHS Adaptive Structures Conference
10t. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-1725.

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Berg, Dale E., Jose R. Zayas, Donald W. Lobitz, C. P. van Dam, Raymond Chow, and Jonathon P. Baker. "Active Aerodynamic Load Control of Wind Turbine Blades." In ASME/JSME 2007 5th Joint Fluids Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/fedsm2007-37604.

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The cost of wind-generated electricity can be reduced by mitigating fatigue loads acting on the rotor blades of wind turbines. One way to accomplish this is with active aerodynamic load control devices that supplement the load control obtainable with current full-span pitch control. Thin airfoil theory suggests that such devices will be more effective if they are located near the blade trailing edge. While considerable effort in Europe is concentrating on the capability of conventional trailing edge flaps to control these loads, our effort is concentrating on very small devices, called microtabs, that produce similar effects. This paper discusses the work we have done on microtabs, including a recent simulation that illustrates the large impact these small devices can exert on a blade. Although microtabs show promise for this application, significant challenges must be overcome before they can be demonstrated to be a viable, cost-effective technology.
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Pirau, Sorin, Brandon Liberi, Natasha Barbely, and Narayanan Komerath. "Generalizing Prediction of Bluff Body Aerodynamic Load Maps." In ASME/JSME/KSME 2015 Joint Fluids Engineering Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/ajkfluids2015-15542.

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The Continuous Rotation method enables efficient definition of all aerodynamic load components on bodies of arbitrary shape for arbitrary attitudes. This is applied to several bluff body shapes including cylinders, a cuboid, a flat plate and a porous box. Rate effects and unsteadiness are shown to be negligible using a cylinder of aspect ratio 1. The genesis of the side force on the yawed cylinder, and the differences between rough and smooth cylinders, are derived from comparisons between experiments and diagnostic computations with an unsteady Navier-Stokes solver. Interpolating Fourier coefficients of the azimuthal load variation appears to be viable to generalize loads on cylinders of varying aspect ratio. A large variation is seen for aspect ratio 0.5 to 1, with a more gradual transition to ‘high aspect ratio’ features beyond aspect ratio 2.
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Thakur, Shilpa, and Nilanjan Saha. "Load Reduction on Offshore Wind Turbines by Aerodynamic Flaps." In ASME 2017 36th International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/omae2017-61308.

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This paper focuses on load reduction by implementing controllable trailing-edge flaps on an offshore wind turbine (OWT) supported on different fixed bottom structures in various water depths. The benchmark NREL 5-MW offshore horizontal axis wind turbine is used as a reference. This work utilizes the wind turbine simulation tool FAST with coupled stochastic aerodynamic-hydrodynamic analysis for obtaining the responses. The flap is controlled using an external dynamic link library through PID controller. Blade element momentum (BEM) theory and Morison equation are used to compute the aerodynamic and hydrodynamic loads, respectively. BEM theory is presently modified to account for unsteady effects of flaps along the blade span. Variation in force coefficients is shown due to unsteady effects of flaps. The present analysis results show reduction up to 8–29% in blade loads for the turbine with different support structures on implementing controllable trailing edge flaps. Also, an influence of blade load reduction on tower base and nacelle is shown. Tower loads are calculated considering aerodynamic and hydrodynamic loads individually. This study can form the basis for evaluating the performance for large-scale fixed offshore wind turbine rotors.
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DRELA, MARK. "Method for simultaneous wing aerodynamic and structural load prediction." In 7th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2200.

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Budolak, Daniel, Lydia Hantsche, and Erick Rossi De La Fuente. "Strain Sensor Survey for Parachute Canopy Load Measurements." In 26th AIAA Aerodynamic Decelerator Systems Technology Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2022. http://dx.doi.org/10.2514/6.2022-2754.

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Qiang Fang, Yu Yao, and Xiao-Chen Wang. "Disturbance observer design for electric aerodynamic load simulator." In Proceedings of 2005 International Conference on Machine Learning and Cybernetics. IEEE, 2005. http://dx.doi.org/10.1109/icmlc.2005.1527147.

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Yoonsu Nam, Jinyoung Lee, and Sung Kyung Hong. "Force control system design for aerodynamic load simulator." In Proceedings of 2000 American Control Conference (ACC 2000). IEEE, 2000. http://dx.doi.org/10.1109/acc.2000.879124.

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Reports on the topic "Aerodynamic load"

1

Fine, Neal, Todd Griffith, and Mario Rotea. Active Aerodynamic Load Control for Wind Turbines. Office of Scientific and Technical Information (OSTI), January 2024. http://dx.doi.org/10.2172/2324926.

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Homicz, G. F. Numerical simulation of VAWT stochastic aerodynamic loads produced by atmospheric turbauence: VAWT-SAL code. Office of Scientific and Technical Information (OSTI), September 1991. http://dx.doi.org/10.2172/5177561.

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Cicolani, Luigi S., Jeffery Lusardi, Lloyd D. Greaves, Dwight Robinson, Aviv Rosen, and Rueben Raz. Flight Test Results for the Motions and Aerodynamics of a Cargo Container and a Cylindrical Slung Load. Fort Belvoir, VA: Defense Technical Information Center, April 2010. http://dx.doi.org/10.21236/ada517702.

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Luttges, Marvin W., Mark S. Miller, Michael C. Robinson, Derek E. Shipley, and David A. Simms. Evidence That Aerodynamic Effects, Including Dynamic Stall, Dictate HAWT Structure Loads and Power Generation in Highly Transient Time Frames. Office of Scientific and Technical Information (OSTI), August 1994. http://dx.doi.org/10.2172/10177826.

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