Relevant bibliographies by topics / Flutter

Academic literature on the topic 'Flutter'

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

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Journal articles on the topic "Flutter"

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Xing, Tong, and Liang Fu. "A Study of a Miniature Modularized Electro-Hydraulic High-Frequency Flutter." Applied Mechanics and Materials 201-202 (October 2012): 360–63. http://dx.doi.org/10.4028/www.scientific.net/amm.201-202.360.

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In order to solve the problem that traditional flutters can’t reach the requirements of vibration-assisted machining (VAM), a miniature modularized electro-hydraulic high-frequency flutter was proposed, which can output large force in high frequency. The structure and working principle of the flutter were elaborated in this paper. The equations of the valve in this flutter can be obtained based on equations of tradition valves, which established the mathematical model of the flutter. The flutter output waveforms were analysed by MATLAB in different input frequencies. The simulation results show that the flutter amplitude reach the maximum value in resonant frequency.
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GUO, TONGQING, ZHILIANG LU, and YONGJIAN WU. "A TIME-DOMAIN METHOD FOR TRANSONIC FLUTTER ANALYSIS WITH MULTIDIRECTIONAL COUPLED VIBRATIONS." Modern Physics Letters B 23, no. 03 (January 30, 2009): 453–56. http://dx.doi.org/10.1142/s0217984909018631.

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Gridgen is employed for static multi-block grid generation. A rapid deforming technique is employed for dynamic grids. Flutters are numerically analyzed in the time domain with a coupled solution of unsteady Euler equations and structural equations of motion. Based on variable stiffness method of transonic flutter analysis, a time-domain method of transonic flutter analysis with multi-directional coupled vibrations is develpoed. For completeness, flutter characteristics of a wing model with winglets and an aircraft model with external stores are numerically analyzed.
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Weber LeBrun, Emily E. "Flutter, Flutter." Obstetrics & Gynecology 127, no. 2 (February 2016): 400. http://dx.doi.org/10.1097/aog.0000000000001249.

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Cavallaro, Joseph, James Haran, and Chase Donaldson. "All That Flutters is Not Flutter." Annals of Emergency Medicine 76, no. 1 (July 2020): 46–49. http://dx.doi.org/10.1016/j.annemergmed.2019.12.013.

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Kurkov, A. P., and O. Mehmed. "Optical Measurements of Unducted Fan Flutter." Journal of Turbomachinery 115, no. 1 (January 1, 1993): 189–96. http://dx.doi.org/10.1115/1.2929206.

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The paper describes a nonintrusive optical method for measuring flutter vibrations in unducted fan or propeller rotors and provides detailed spectral results for two flutter modes of a scaled unducted fan. The measurements were obtained in a high-speed wind tunnel. A single-rotor and a dual-rotor counterrotating configuration of the model were tested; however, only the forward rotor of the counterrotating configuration fluttered. Conventional strain gages were used to obtain flutter frequency; optical data provided complete phase results and an indication of the flutter mode shape through the ratio of the leading- to trailing-edge flutter amplitudes near the blade tip. In the transonic regime the flutter exhibited some features that are usually associated with nonlinear vibrations. Experimental mode shape and frequencies were compared with calculated values that included centrifugal effects.
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Mayell, Marcus R., Nicolaus T. Dulworth, Brandon Cudequest, and Robin Glosemeyer Petrone. "One acoustician’s defect is another artist’s feature: Simulating real flutter for an art installation." Journal of the Acoustical Society of America 152, no. 4 (October 2022): A210. http://dx.doi.org/10.1121/10.0016034.

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Flutter is generally considered an acoustical defect – the timbral distortions and rhythmic nature can be distracting, annoying, or downright disruptive. The paper recontextualizes flutter as a compositional tool for sound art, particularly when the flutter of existing rooms is used for site-specific installations. Due to the global COVID-19 pandemic, the artist was unable to travel, allowing us to visit the site and take several room impulse responses. The measured spaces were parallelpiped, sound reflective, and fluttery. To give the artist creative flexibility, we simulated the rooms for an extended range of source and receiver locations informed by the in-situ measurements. This paper will discuss our calibration and modeling techniques to simulate flutter and reverberation coloration in real rooms, which is non-trivial for image source methods or ray-based software.
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Raut, Roshan, Prashanta Bajracharya, Man Bahadur KC, Murari Dhungana, Mukunda Sharma, Surakshya Joshi, Prashanta Bajracharya, Kunjang Sherpa, Mandita Chamlagain, and Sujeeb Rajbhandari. "Efficacy and Safety of Focal Atrial Tachycardia and Typical Atrial Flutter Ablation in Nepal-A Single Center Experience." Nepalese Heart Journal 18, no. 1 (April 30, 2021): 25–28. http://dx.doi.org/10.3126/njh.v18i1.36776.

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Background and Aims: Atrial tachycardia is classified as focal atrial tachycardia or macro-reentrant atrial tachycardia. Macro-reentrant atrial tachycardia involves large circuit and is also called atrial flutter in which cavotricuspid isthmus dependent flutter, also called typical atrial flutter is the most common. The aim of this study is to report the efficacy and safety of catheter ablations of these arrhythmias, for the first time in Nepal. Methods: This is a retrospective observational study of the patients who underwent electrophysiological study with ablation for focal atrial tachycardia and typical atrial flutters at Shahid Gangalal National Heart Center (SGNHC) from March, 2015 to February 2020. Results: Altogether, 49 patients, 27 for focal atrial tachycardia and 22 for typical atrial flutter, underwent electrophysiology study with intent to ablation. In two patients, atrial tachycardia could not be induced, therefore 25 patients underwent ablation for atrial tachycardia. Out of 25 patients, the successful ablation achieved in 24 patients (96%) with recurrence in three patients (12%), with no major complications. Atrial tachycardia more commonly originated from right atrium than the left atrium (68% vs. 32%). Among 22 patients who underwent cavotricuspid isthmus ablation for typical atrial flutter; successful ablation achieved in 21 patients (95%) with recurrence in two patients (9%) and a single case of access site hematoma. Counterclockwise flutter was found to be more common than clockwise flutter (91% vs. 9%). Conclusion: In SGNHC, the ablations of focal atrial tachycardia and the typical atrial flutter has a high success and low complication rate.
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Byun, Junghwan, Minjo Park, Sang-Min Baek, Jaeyoung Yoon, Woongbae Kim, Byeongmoon Lee, Yongtaek Hong, and Kyu-Jin Cho. "Underwater maneuvering of robotic sheets through buoyancy-mediated active flutter." Science Robotics 6, no. 53 (April 21, 2021): eabe0637. http://dx.doi.org/10.1126/scirobotics.abe0637.

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Falling leaves flutter from side to side due to passive and intrinsic fluid-body coupling. Exploiting the dynamics of passive fluttering could lead to fresh perspectives for the locomotion and manipulation of thin, planar objects in fluid environments. Here, we show that the time-varying density distribution within a thin, planar body effectively elicits minimal momentum control to reorient the principal flutter axis and propel itself via directional fluttery motions. We validated the principle by developing a swimming leaf with a soft skin that can modulate local buoyancy distributions for active flutter dynamics. To show generality and field applicability, we demonstrated underwater maneuvering and manipulation of adhesive and oil-skimming sheets for environmental remediation. These findings could inspire future intelligent underwater robots and manipulation schemes.
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Nolan, Nathanial S., Scott M. Koerber, and Sudarshan Balla. "Pseudoatrial Flutter Waves—When a Flutter Is Not a Flutter." JAMA Internal Medicine 176, no. 3 (March 1, 2016): 298. http://dx.doi.org/10.1001/jamainternmed.2015.8315.

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Matsumoto, M., F. Yoshizumi, T. Yabutani, K. Abe, and N. Nakajima. "Flutter stabilization and heaving-branch flutter." Journal of Wind Engineering and Industrial Aerodynamics 83, no. 1-3 (November 1999): 289–99. http://dx.doi.org/10.1016/s0167-6105(99)00079-3.

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Dissertations / Theses on the topic "Flutter"

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Balevi, Birtan Taner. "Flutter Analysis And Simulated Flutter Test Of Wings." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12615016/index.pdf.

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Flutter is a dynamic instability which can result in catastrophic failures of an air vehicle. Preventing flutter can be an important factor in the aircraft design, affecting the structural design. Thus, the weight and performance of the aircraft is also being affected. Understanding the role of each design factor of a wing on the onset of flutter can help designers on the flutter clearance of the aircraft. Analysis to predict flutter, ground vibration tests and flight flutter tests, which are performed to verify that the dedicated flight envelope is clear from flutter, are the most important certification processes in modern aviation. Flight flutter testing is a very expensive process. In flight flutter tests the air vehicle is instrumentated with exciters, accelerometers and transmitters to send the test data simultaneously to the ground station to be analyzed. Since flutter is a very severe instability, which develops suddenly, the data should be followed carefully by the engineers at the ground station and feedback should be provided to the pilot urgently when needed. Low test step numbers per flight, increases the cost of flutter testing. Increasing efforts in pre-flight test processes in flutter prediction may narrow the flight flutter test steps and decrease the costs. In this study, flutter prediction methods are investigated to aid the flutter test process. For incompressible flight conditions, some sample problems are solved using typical section model. Flutter solutions of a simple 3D wing are also performed via a coupled finite element linear aerodynamics approach using the commercial tool Nastran. 3D flutter solutions of the wing are compared with the typical section solutions to see how close can the typical section method predict flutter compared to the flutter analyis using the three dimensional wing model. A simulated flutter test method is introduced utilizing the two dimensional typical section method. It is shown that with a simple two dimensional typical section method, flutter test simulation can be performed successfully as long as the typical section model approximates the dynamic properties of the wing closely.
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Khalak, Asif 1972. "Parametric dependencies of aeroengine flutter for flutter clearance applications." Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/8818.

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Thesis (Ph.D.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2000.
"September 2000."
Includes bibliographical references (p. 223-228).
This thesis describes the effects of operational parameters upon aeroengine flutter stability. The study is composed of three parts: theoretical development of relevant parameters, exploration of a computational model, and analysis of fully scaled test data. Results from these studies are used to develop a rational flutter clearance methodology-a test procedure to ensure flutter-free operation. It is shown, under conditions relevant to aeroengines, that four nondimensional parameters are necessary and sufficient for flutter stability assessment of a given rotor geometry. We introduce a new parameter, termed the reduced damping, g/p *, which collapses the combined effects of mechanical damping and mass ratio (blade mass to fluid inertia). Furthermore, the introduction of the compressible reduced frequency, K*, makes it possible to uniquely separate the corrected performance map from the non-dimensional operating environment (including inlet temperature and pressure). Simultaneous plots of the performance map of corrected mass flow and corrected speed, (^.mc, Nc), with the (K*, g/p*) map provide a dimensionally complete and fully integrated view of flutter stability, as demonstrated in the context of a historic multimission engine. A parametric, computational study was conducted using a 2D, linearized unsteady, compressible, potential flow model of a vibrating cascade. This study showed the independent effects of Mach number, inlet flow angle, and reduced frequency upon flutter stability in terms of critical reduced damping, which corroborates the 4D view of flutter stability. Test data from a full-scale transonic fan, spanning the full 4D parameter space, were also analyzed. A novel boundary fitting tool was developed for data processing, which can handle the generic case of sparse, multidimensional, binary data. The results indicate that the inlet pressure does not alone determine the flight condition effects upon flutter, which necessitates the use of the complete 4D parameter set. Such a complete view of the flutter boundary is constructed, and sensitivities with respect to various parameters are estimated. A rational flutter clearance procedure is proposed. Trends in K* and g/p* allow one to rapidly determine the worst-cases for testing a given design. One may also use sensitivities to extend the results of sea level static (SLS) testing, if the worst case is relatively close to the SLS condition.
by Asif Khalak.
Ph.D.
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Barman, Emelie. "Aerodynamics of Flutter." Thesis, KTH, Mekanik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-34152.

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The unsteady ow around an aerofoil placed in a uniform ow stream with an angle of attack is investigated, under the assumption of inviscid, incompressible, two-dimensional flow. In particular, a function of the velocity jump over the wake is achieved, where this function depends on the horizontal displacement and time. The aerofoil geometry is represented by two arbitrary functions, one for the upper and one for the lower side of the aerofoil. These functions are dependent on time, hence the aerofoil can perform oscillating movement, which is the case when subjected to utter. The governing equations for the ow are the Euler equations. By assuming thin aerofoil, small angle of attack and that the perturbation of the wake is small, the problem is linearised. It is shown that the linearised Euler equations can be rewritten as the Cauchy-Riemann equations, and an analytic function exists where its real part is the horizontal velocity component and its imaginary part is the vertical velocity component with opposite sign. The ow eld is then investigated in the complex plane by making an appropriate branch cut removing all discontinuities, and with restrictions on the analytic function such that the kinematic and boundary conditions are satis ed. By using Cauchy's integral formula an expression for the anti-symmetric part of the analytic function is achieved. A general expression for the velocity jump over the wake is obtained, which is applied to the speci c case of harmonic oscillations for a symmetric aerofoil. In the end three types of utter is investigated; twisting oscillations around the centre of stiness, vertical oscillation, and aileron flutter.
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Zhao, Fanzhou. "Embedded blade row flutter." Thesis, Imperial College London, 2016. http://hdl.handle.net/10044/1/51151.

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Modern gas turbine design continues to drive towards improved performance, reduced weight and reduced cost. This trend of aero-engine design results in thinned blade aerofoils which are more prone to aeroelastic problems such as flutter. Whilst extensive work has been conducted to study the flutter of isolated turbomachinery blades, the number of research concerning the unsteady interactions between the blade vibration, the resulting acoustic reflections and flutter is very limited. In this thesis, the flutter of such embedded blade rows is studied to gain understanding as for why and how such interactions can result in flutter. It is shown that this type of flutter instability can occur for single stage fan blades and multi-stage core compressors. Unsteady CFD computations are carried out to study the influence of acoustic reflections from the intake on flutter of a fan blade. It is shown that the accurate prediction of flutter boundary for a fan blade requires modelling of the intake. Different intakes can produce different flutter boundaries for the same fan blade and the resulting flutter boundary is a function of the intake geometry in front of it. The above finding, which has also been demonstrated experimentally, is a result of acoustic reflections from the intake. Through in-depth post-processing of the results obtained from wave-splitting of the unsteady CFD solutions, the relationship between the phase and amplitude of the reflected acoustic waves and flutter stability of the blade is established. By using an analytical approach to calculate the propagation and reflection of acoustic waves in the intake, a novel low- fidelity model capable of evaluating the susceptibility of a fan blade to flutter is proposed. The proposed model works in a similar fashion to the Campbell diagram, which allows one to identify the region (in compressor map) where flutter is likely to occur at early design stages of an engine. In the second part of this thesis, the influence of acoustic reflections from adjacent blade rows on flutter stability of an embedded rotor in a multi-stage compressor is studied using unsteady CFD computations. It is shown that reflections of acoustic waves, generated by the rotor blade vibration, from the adjacent blade rows have a significant impact on the flutter stability of the embedded rotor, and the computations using the isolated rotor can lead to significant over-optimistic predictions of the flutter boundary. Based on the understanding gained, an alternative strategy, aiming to reduce the computational cost, for the flutter analysis of such embedded blades is proposed. The method works by modelling the propagation and reflection of acoustic waves at the adjacent blade rows using an analytical method, whereby flutter computations of the embedded rotor can be performed in an isolated fashion by imposing the calculated reflected waves as unsteady plane sources. Computations using the proposed model can lead to two orders of magnitude reduction in computational cost compared with time domain full annulus multi-row computations. The computed results using the developed low-fidelity model show good correlation with the results obtained using full annulus multi-row models.
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Dong, Bonian. "Numerical simulation of wakes, blade-vortex interaction, flutter, and flutter suppression by feedback control." Diss., This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-07282008-134810/.

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Chernysheva, Olga V. "Flutter in sectored turbine vanes." Doctoral thesis, KTH, Energy Technology, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3737.

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In order to eliminate or reduce vibration problems inturbomachines without a high increase in the complexity of thevibratory behavior, the adjacent airfoils around the wheel areoften mechanically connected together with lacing wires, tip orpart-span shrouds in a number of identical sectors. Although anaerodynamic stabilizing effect of tying airfoils together ingroups on the whole cascade is indicated by numerical andexperimental studies, for some operating conditions suchsectored vane cascade can still remain unstable.

The goal of the present work is to investigate thepossibilities of a sectored vane cascade to undergoself-excited vibrations or flutter. The presented method forpredicting the aerodynamic response of a sectored vane cascadeis based on the aerodynamic work influence coefficientrepresentation of freestanding blade cascade. The sectored vaneanalysis assumes that the vibration frequency is the same forall blades in the sectored vane, while the vibration amplitudesand mode shapes can be different for each individual blade inthe sector. Additionally, the vibration frequency as well asthe amplitudes and mode shapes are supposed to be known.

The aerodynamic analysis of freestanding blade cascade isperformed with twodimensional inviscid linearized flow model.As far as feasible the study is supported by non-linear flowmodel analysis as well as by performing comparisons againstavailable experimental data in order to minimize theuncertainties of the numerical modeling on the physicalconclusions of the study.

As has been shown for the freestanding low-pressure turbineblade, the blade mode shape gives an important contributioninto the aerodynamic stability of the cascade. During thepreliminary design, it has been recommended to take intoaccount the mode shape as well rather than only reducedfrequency. In the present work further investigation using foursignificantly different turbine geometries makes these findingsmore general, independent from the low-pressure turbine bladegeometry. The investigation also continues towards a sectoredvane cascade. A parametrical analysis summarizing the effect ofthe reduced frequency and real sector mode shape is carried outfor a low-pressure sectored vane cascade for differentvibration amplitude distributions between the airfoils in thesector as well as different numbers of the airfoils in thesector. Critical (towards flutter) reduced frequency maps areprovided for torsion- and bending-dominated sectored vane modeshapes. Utilizing such maps at the early design stages helps toimprove the aerodynamic stability of low-pressure sectoredvanes.

A special emphasis in the present work is put on theimportance for the chosen unsteady inviscid flow model to bewell-posed during numerical calculations. The necessity for thecorrect simulation of the far-field boundary conditions indefining the stability margin of the blade rows isdemonstrated. Existing and new-developed boundary conditionsare described. It is shown that the result of numerical flowcalculations is dependent more on the quality of boundaryconditions, and less on the physical extension of thecomputational domain. Keywords: Turbomachinery, Aerodynamics,Unsteady CFD, Design, Flutter, Low-Pressure Turbine, Blade ModeShape, Critical Reduced Frequency, Sectored Vane Mode Shape,Vibration Amplitude Distribution, Far-field 2D Non-ReflectingBoundary Conditions. omain.

Keywords:Turbomachinery, Aerodynamics, Unsteady CFD,Design, Flutter, Low-Pressure Turbine, Blade Mode Shape,Critical Reduced Frequency, Sectored Vane Mode Shape, VibrationAmplitude Distribution, Far-field 2D Non-Reflecting BoundaryConditions.

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Akbari, Mohammad Hadi. "Flutter evaluation of an airfoil." Thesis, McGill University, 1993. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=69529.

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The problem of flutter is first introduced. The equations of motion of an airfoil with two degrees of freedom, in pitch and plunge, are obtained. Then, the unsteady aerodynamic theories for different flow regimes are presented. The traditional solutions to the flutter problem, namely, the p-k and U-g methods, are formulated, and the Laplace transformation method for flutter analysis is also introduced. Then, the effect of different design parameters of an airfoil on the flutter speed is analyzed, both in the incompressible and transonic regimes. Furthermore, the effect of the relative values of the design parameters on the occurrence of flutter is investigated. Finally, some general conclusions regarding the above-mentioned phenomena are derived. The goal of this work is the fact that, the unsteady aerodynamic data has been used, both in the incompressible and transonic regimes, and, therefore, the obtained results are fairly precise.
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Shao, Lin, and 邵琳. "Flutter of a cantilevered plate." Thesis, The University of Hong Kong (Pokfulam, Hong Kong), 2010. http://hub.hku.hk/bib/B4559031X.

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Duchesne, Laurent Guillaume. "Advanced techniques for flutter clearance." Thesis, Massachusetts Institute of Technology, 1997. http://hdl.handle.net/1721.1/49966.

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Perrocheau, Mathilde. "Flutter Prediction in Transonic Regime." Thesis, KTH, Flygdynamik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-234840.

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The flutter is a dangerous aeroelastic instability that can cause dramatic failures. It is important to evaluate in which conditions it can occur to ensure the safety of the pilots and the passengers. As flight tests are very expensive and hazardous, the need for efficient and trustworthy numerical tools becomes essential. This report focuses on two methods to predict the flutter conditions in the transonic domain. To evaluate the accuracy of these tools, their results are compared to experimental data gathered during a wind-tunnel test. The influence of the Mach number and the angle of attack on the flutter conditions is studied and physical explanations are put forward.
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Books on the topic "Flutter"

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Flutter. Toronto: Mansfield Press, 2008.

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Flutter. 2nd ed. [Charleston, S.C.]: [CreateSpace], 2010.

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Flutter. New York: Random House Books for Young Readers, 2012.

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Zammetti, Frank. Practical Flutter. Berkeley, CA: Apress, 2019. http://dx.doi.org/10.1007/978-1-4842-4972-7.

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Cheng, Fu. Flutter Recipes. Berkeley, CA: Apress, 2019. http://dx.doi.org/10.1007/978-1-4842-4982-6.

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Cosgrove, Stephen. Flutter fly. [U.S.]: American Value Tales, 1994.

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McLauchlan, Amy. Flutter-bys. Belfast: Lapwing Pub., 2011.

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Markovich, Natasha. Flutter: Kruto, blin. Moskva: RIPOL klassik, 2006.

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ill, Prebenna David, ed. Flutter by, butterfly. [New York]: CTW Books, 1998.

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Clyne, Densey. Flutter by, butterfly. Milwaukee, Wis: Gareth Stevens Publishing, 1998.

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Book chapters on the topic "Flutter"

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Tan, Manuel. "Flutter." In New Masters of Flash, 380–411. Berkeley, CA: Apress, 2001. http://dx.doi.org/10.1007/978-1-4302-5143-9_12.

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Weik, Martin H. "flutter." In Computer Science and Communications Dictionary, 625. Boston, MA: Springer US, 2000. http://dx.doi.org/10.1007/1-4020-0613-6_7368.

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Desnick, Robert J., Orlando Guntinas-Lichius, George W. Padberg, Gustav Schonfeld, Xiaobo Lin, Maurizio Averna, Pin Yue, et al. "Flutter." In Encyclopedia of Molecular Mechanisms of Disease, 666. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-29676-8_9187.

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Mar, Philip, and Rakesh Gopinathannair. "Atypical Flutter: Peri-Mitral Flutter." In Cardiac Electrophysiology, 311–13. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-28533-3_76.

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Tyagi, Priyanka. "Flutter Widgets." In Pragmatic Flutter, 63–86. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003104636-6.

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Tyagi, Priyanka. "Flutter Themes." In Pragmatic Flutter, 153–68. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003104636-10.

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Zammetti, Frank. "Flutter: A Gentle Introduction." In Practical Flutter, 1–36. Berkeley, CA: Apress, 2019. http://dx.doi.org/10.1007/978-1-4842-4972-7_1.

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Zammetti, Frank. "Hitting the Bullseye with Dart." In Practical Flutter, 37–81. Berkeley, CA: Apress, 2019. http://dx.doi.org/10.1007/978-1-4842-4972-7_2.

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Zammetti, Frank. "Say Hello to My Little Friend: Flutter, Part I." In Practical Flutter, 83–134. Berkeley, CA: Apress, 2019. http://dx.doi.org/10.1007/978-1-4842-4972-7_3.

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Zammetti, Frank. "Say Hello to My Little Friend: Flutter, Part II." In Practical Flutter, 135–77. Berkeley, CA: Apress, 2019. http://dx.doi.org/10.1007/978-1-4842-4972-7_4.

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Conference papers on the topic "Flutter"

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Williamson, John, and Lorna M. Brown. "Flutter." In the 7th ACM conference. New York, New York, USA: ACM Press, 2008. http://dx.doi.org/10.1145/1394445.1394461.

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Profita, Halley, Nicholas Farrow, and Nikolaus Correll. "Flutter." In TEI '15: Ninth International Conference on Tangible, Embedded, and Embodied Interaction. New York, NY, USA: ACM, 2015. http://dx.doi.org/10.1145/2677199.2680586.

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Roizner, Federico, Daniella E. Raveh, and Moti Karpel. "Safe Flutter Tests Using Parametric Flutter Margins." In 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0701.

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Kurkov, Anatole P., and Oral Mehmed. "Optical Measurements of Unducted Fan Flutter." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-019.

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The paper describes a nonintrusive optical method for measuring flutter vibrations in unducted fan or propeller rotors and provides detailed spectral results for two flutter modes of a scaled unducted fan. The measurements were obtained in a high-speed wind tunnel. A single-rotor and a dual-rotor counterrotating configuration of the model were tested; however, only the forward rotor of the counterrotating configuration fluttered. Conventional strain gages were used to obtain flutter frequency; optical data provided complete phase results and an indication of the flutter mode shape through the ratio of the leading- to trailing-edge flutter amplitudes near the blade tip. In the transonic regime the flutter exhibited some features that are usually associated with nonlinear vibrations. Experimental mode shape and frequencies were compared with calculated values that included centrifugal effects.
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Chang, Young B., Chang H. Cho, and Peter M. Moretti. "Edge Flutter." In ASME 1999 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/imece1999-0224.

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Abstract During manufacturing processes of thin materials (called webs) such as papers, photographic films, and magnetic films, the free edges of a web can vibrate violently due to the airflow in the cross direction. A traveling-wave analysis was done based on linear potential flow theory, and the critical flow velocity, wave velocity, wavelength and flutter frequency were predicted. Experimental verification was done in a wind tunnel built around a web-translating machine. Two laser-Doppler vibrometers were used for non-contact measurement of wave characteristics. For flexible webs, the theory and test results show good agreement. Test results for stiff webs, however, deviate from the prediction.
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Fucun, Qu. "Determination of Flutter Boundary by Robust Flutter Margin Method." In 2012 International Conference on Industrial Control and Electronics Engineering (ICICEE). IEEE, 2012. http://dx.doi.org/10.1109/icicee.2012.280.

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Maheux, Sébastien, Sébastien Langlois, and Frédéric Légeron. "Flutter Analysis Using Quasi-Steady Time-Domain Flutter Derivatives." In IABSE Congress, New York, New York 2019: The Evolving Metropolis. Zurich, Switzerland: International Association for Bridge and Structural Engineering (IABSE), 2019. http://dx.doi.org/10.2749/newyork.2019.2664.

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<p>To be able to perform nonlinear flutter analyses for bridges, time‐domain approaches should be used instead of Scanlan’s formulation of self‐excited forces. Thus, this paper addresses the development and validation of a modified quasi‐steady time‐domain model similar to Scanlan’s approach that is based on the velocity and acceleration of the bridge deck. In this formulation, quasi‐steady time‐domain flutter derivatives measured in the wind tunnel through forced‐vibration tests at absolute constant velocity and acceleration are used. For this, a unique test rig, which can be used either for free‐ or forced‐vibration tests, was utilized. By measuring the time‐domain flutter derivatives of the Great Belt Bridge, their nondimensionalization with respect to the bridge‐deck width, velocity and acceleration of the deck is validated. Then, time‐domain flutter analyses are performed using this new model. They agree with the experimental critical speed and the prediction using Scanlan’s model.</p>
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Gali, Sai Vishal, Todd Goehmann, and Cristina Riso. "Predicting Whirl Flutter Bifurcations Using Pre-Flutter Output Data." In AIAA SCITECH 2023 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-1308.

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DAVIS, GARY, and ODDVAR BENDIKSEN. "Transonic panel flutter." In 34th Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1476.

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Wu, Zhigang, and Jonathan E. Cooper. "Active Flutter Suppression Combining the Receptance Method and Flutter Margin." In 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1227.

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Reports on the topic "Flutter"

1

Busan, Ron. Flutter Model Technology. Fort Belvoir, VA: Defense Technical Information Center, January 1998. http://dx.doi.org/10.21236/ada340820.

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Casey, J. K. Empirical Flutter Prediction Method. Fort Belvoir, VA: Defense Technical Information Center, March 1988. http://dx.doi.org/10.21236/ada195699.

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Krener, A. J. Bifurcations of Control Systems with Application to Flutter. Fort Belvoir, VA: Defense Technical Information Center, January 2001. http://dx.doi.org/10.21236/ada430327.

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Klyde, David, Chuck Harris, Peter M. Thompson, and Edward N. Bachelder. System Identification Methods for Improving Flutter Flight Test Techniques. Fort Belvoir, VA: Defense Technical Information Center, August 2004. http://dx.doi.org/10.21236/ada426452.

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Mottershead, John E., and J. E. Cooper. Extension of Flutter Boundaries Using In-Flight Receptance Data. Fort Belvoir, VA: Defense Technical Information Center, November 2012. http://dx.doi.org/10.21236/ada571493.

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Kokotovic, Petar, Richard Murray, Arthur Krener, and James Paduano. Robust Nonlinear Control of Stall and Flutter in Aeroengines. Fort Belvoir, VA: Defense Technical Information Center, June 2000. http://dx.doi.org/10.21236/ada387455.

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Armstrong, William D., William R. Lindberg, John E. McInroy, and Jonathan W. Naughton. Active Flutter Suppression Using Cooperative, High Frequency, Dynamic-Resonant Aero-Effectors. Fort Belvoir, VA: Defense Technical Information Center, December 2006. http://dx.doi.org/10.21236/ada463491.

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Dowell, Earl H., and Kenneth C. Hall. Theoretical Prediction of Limit Cycle Oscillations in Support of Flight Flutter Testing. Fort Belvoir, VA: Defense Technical Information Center, August 2003. http://dx.doi.org/10.21236/ada426408.

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Farhat, Charles. Real Time Predictive Flutter Analysis and Continuous Parameter Identification of Accelerating Aircraft. Fort Belvoir, VA: Defense Technical Information Center, September 1998. http://dx.doi.org/10.21236/ada361695.

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Striz, Alfred G. Influence of Structural and Aerodynamic Modeling on Flutter Analysis and Structural Optimization. Fort Belvoir, VA: Defense Technical Information Center, June 1991. http://dx.doi.org/10.21236/ada248487.

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