Relevant bibliographies by topics / Subsonic flutter

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

Academic literature on the topic 'Subsonic flutter'

Author: Grafiati
Published: 4 June 2021
Last updated: 28 July 2025

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Journal articles on the topic "Subsonic flutter"

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Chi, R. M., and A. V. Srinivasan. "Some Recent Advances in the Understanding and Prediction of Turbomachine Subsonic Stall Flutter." Journal of Engineering for Gas Turbines and Power 107, no. 2 (1985): 408–17. http://dx.doi.org/10.1115/1.3239741.

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In this paper, some recent advances in the understanding and prediction of subsonic flutter of jet engine fan rotor blades are reviewed. Among the topics discussed are (i) the experimental evidence of mistuning in flutter responses, (ii) new and promising unsteady aerodynamic models for subsonic stall flutter prediction, (iii) an overview of flutter prediction methodologies, and (iv) a new research effort directed toward understanding the mistuning effect on subsonic stall flutter of shrouded fans. A particular shrouded fan of advanced design is examined in the detailed technical discussion.
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Moosavi, M. R., A. R. Naddaf Oskouei, and A. Khelil. "Flutter of subsonic wing." Thin-Walled Structures 43, no. 4 (2005): 617–27. http://dx.doi.org/10.1016/j.tws.2004.10.001.

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Jweeg, Muhsin J., Shokat Al-Tornachi, and Tariq Samir Talib. "FLUTTER SPEED LIMITS OF SUBSONIC WINGS." Journal of Engineering 18, no. 2 (2023): 163–83. http://dx.doi.org/10.31026/j.eng.2012.02.03.

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Flutter is a phenomenon resulting from the interaction between aerodynamic and structural dynamic forces and may lead to a destructive instability. The aerodynamic forces on an oscillating airfoil combination of two independent degrees of freedom have been determined. The problem resolves itself into the solution of certain definite integrals, which have been identified as Theodorsen functions. The theory, being based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing-ection theory relating to the steady case. The mechanism of aerodynamic instabilit
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Dinulović, Mirko, Aleksandar Benign, and Boško Rašuo. "Composite Fins Subsonic Flutter Prediction Based on Machine Learning." Aerospace 11, no. 1 (2023): 26. http://dx.doi.org/10.3390/aerospace11010026.

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In the present work, the potential application of machine learning techniques in the flutter prediction of composite materials missile fins is investigated. The flutter velocity data set required for different fin aerodynamic geometries and materials is generated using a hybrid data collection method: from the wind tunnel experiments at flows ranging from 5 to 30 m/s at Re = 300,000 to 500,000, whereas synthetic data is collected using modified NACA flutter boundary model. Once the flutter data are collected, different regression algorithms were investigated, and the results were compared in t
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Yaman, Kemal. "Subsonic Flutter of Cantilever Rectangular PC Plate Structure." International Journal of Aerospace Engineering 2016 (2016): 1–10. http://dx.doi.org/10.1155/2016/9212364.

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Flutter characteristics of cantilever rectangular flexible plate structure under incompressible flow regime are investigated by comparing the results of commercial flutter analysis program ZAERO©with wind tunnel tests conducted in Ankara Wind Tunnel (ART). A rectangular polycarbonate (PC) plate, 5 × 125 × 1000 mm in dimension, is used for both numerical and experimental investigations. Analysis and test results are very compatible with each other. A comparison between two different solution methods (g-methodandk-method) of ZAERO©is also done. It is seen that thek-methodgives a closer result th
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Zyl, L. van. "Low frequency behaviour of the subsonic doublet lattice method." Aeronautical Journal 109, no. 1096 (2005): 285–71. http://dx.doi.org/10.1017/s0001924000000749.

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Abstract The results of the subsonic doublet lattice method (DLM), i.e. generalised unsteady aerodynamic forces (GAFs) at a set of reduced frequencies, are often used as input to the solution of the flutter equation. Solutions of the flutter equation are usually required at many more reduced frequencies than GAFs are calculated for by the DLM and some form of interpolation is therefore required. In the p-k formulation of Rodden, Harder and Bellinger, the imaginary part of the GAFs appear as QI/k, i.e. the imaginary part of the GAFs divided by the reduced frequency. In the case of real (i.e. no
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Kobayashi, H. "Annular Cascade Study of Low Back-Pressure Supersonic Fan Blade Flutter." Journal of Turbomachinery 112, no. 4 (1990): 768–77. http://dx.doi.org/10.1115/1.2927720.

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Low back-pressure supersonic fan blade flutter in the torsional mode was examined using a controlled-oscillating annular cascade test facility. Precise data of unsteady aerodynamic forces generated by shock wave movement, due to blade oscillation, and the previously measured data of chordwise distributions of unsteady aerodynamic forces acting on an oscillating blade, were joined and, then, the nature of cascade flutter was evaluated. These unsteady aerodynamic forces were measured by direct and indirect pressure measuring methods. Our experiments covered a range of reduced frequencies based o
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Yu, Li, Bin Bin Lv, Hong Tao Guo, Yu Yan, Xing Hua Yang, and Jian Guo Luo. "Research on Transonic Wind Tunnel Flutter Test for a Wing Model." Advanced Materials Research 1006-1007 (August 2014): 26–29. http://dx.doi.org/10.4028/www.scientific.net/amr.1006-1007.26.

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This paper adopts self-designed wing model to conduct flutter test on subsonic and transonic, and obtains flutter characteristic of the model, and the test results are used for calibration and verification of flutter procedures. The sub-critical extrapolation is used to obtain the flutter sub-critical parameters and the direct observation method is used to obtain comparison of results. Error of results obtained by the two approaches does not exceed 5%, and validates reliability of the sub-critical prediction approach in continuous adjusted dynamic pressure flutter test.
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Balakrishnan, A. V. "Subsonic flutter suppression using self-straining actuators." Journal of the Franklin Institute 338, no. 2-3 (2001): 149–70. http://dx.doi.org/10.1016/s0016-0032(00)00088-0.

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Yun, J. M., and J. H. Han. "Development of ground vibration test based flutter emulation technique." Aeronautical Journal 124, no. 1279 (2020): 1436–61. http://dx.doi.org/10.1017/aer.2020.36.

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ABSTRACTIn demand of simpler and alternative ground flutter test, a new technique that emulates flutter on the ground has recently emerged. In this paper, an improvement of the test technique is made and verified through the experimental work. The technique utilizes general ground vibration test (GVT) devices. The key idea is to emulate the distributed unsteady aerodynamic force by using a few concentrated actuator forces; referred to as emulated flutter test (EFT) technique. The EFT module contains two main logics; namely, real-time aerodynamic equivalent force calculator and multi-input-mult
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Dissertations / Theses on the topic "Subsonic flutter"

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Kakkavas, Constantinos. "Computational investigation of subsonic torsional airfoil flutter." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1998. http://handle.dtic.mil/100.2/ADA359731.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, December 1998.<br>"December 1998." Thesis advisor(s): Max F. Platzer, Kevin D. Jones. Includes bibliographical references (p. 89-90). Also available online.
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Alan, Luton J. "Numerical simulations of subsonic aeroelastic behavior and flutter suppression by active control /." This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-03172010-020348/.

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Luton, J. Alan. "Numerical simulations of subsonic aeroelastic behavior and flutter suppression by active control." Thesis, Virginia Tech, 1991. http://hdl.handle.net/10919/41681.

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<p>A method for predicting the unsteady, subsonic, aeroservoelastic response of a wing has been developed. The air, wing, and control surface are considered to be a single dynamical system. All equations are solved simultaneously in the time domain by a predictor-corrector method. The scheme allows nonlinear aerodynamic and structural models to be used and subcritical, critical, and supercritical aeroelastic behavior may be modeled without restrictions to small disturbances or periodic motions. A vortex-lattice method is used to model the aerodynamics. This method accounts for nonlinear effect
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Ferria, Hakim. "Contribution to Numerical and Experimental Studies of Flutter in Space Turbines. Aerodynamic Analysis of Subsonic or Supersonic Flows in Response to a Prescribed Vibratory Mode of the Structure." Phd thesis, Ecole Centrale de Lyon, 2011. http://tel.archives-ouvertes.fr/tel-00677648.

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Modern turbomachines are designed towards thinner, lighter and highly loaded blades. This gives rise to increased sensitivity to flow induced vibrations such as flutter, which leads to structure failure in a short period of time if not sufficiently damped. Although numerical tools are more and more reliable, flutter prediction still depends on a large degree on simplified models. In addition, the critical nature of flutter, resulting in poor welldocumented real cases in the open literature, and the lack of experimental database typical of engine flows make its apprehension even more challengin
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Ly, Eddie, and Eddie Ly@rmit edu au. "Numerical schemes for unsteady transonic flow calculation." RMIT University. Mathematics and Geospacial Sciences, 1999. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20081212.163408.

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An obvious reason for studying unsteady flows is the prediction of the effect of unsteady aerodynamic forces on a flight vehicle, since these effects tend to increase the likelihood of aeroelastic instabilities. This is a major concern in aerodynamic design of aircraft that operate in transonic regime, where the flows are characterised by the presence of adjacent regions of subsonic and supersonic flow, usually accompanied by weak shocks. It has been a common expectation that the numerical approach as an alternative to wind tunnel experiments would become more economical as computers became le
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WU, DENG-YUAN, and 吳登淵. "Optimization of wing structures in subsonic flow under flutter speed constraint." Thesis, 1989. http://ndltd.ncl.edu.tw/handle/80168159350938328520.

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Gibbs, IV Samuel Chad. "Stability of Beams, Plates and Membranes due to Subsonic Aerodynamic Flows and Solar Radiation Pressure." Diss., 2014. http://hdl.handle.net/10161/8678.

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<p>This dissertation explores the stability of beams, plates and membranes due to subsonic aerodynamic flows or solar radiation forces. Beams, plates and membranes are simple structures that may act as building blocks for more complex systems. In this dissertation we explore the stability of these simple structures so that one can predict instabilities in more complex structures. The theoretical models include both linear and nonlinear energy based models for the structural dynamics of the featureless rectangular structures. The structural models are coupled to a vortex lattice model for subso
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Prahallada, J. "Blade Flutter in a Linear Cascade: Unsteady Loads and Flow Features in Subsonic and Transonic Flows." Thesis, 2018. https://etd.iisc.ac.in/handle/2005/4108.

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Vibration related issues like flutter can significantly limit the performance of aircraft engines and cause unwarranted cost and time overruns. The increased demand for more powerful yet compact engines has resulted in the use of relatively thin and long blade rows, which are more susceptible to such vibration related issues. Flutter refers to an aeroelastic instability in which the motion of the blade interacts with the flow to generate the unsteady fluid loads that can sustain or possibly grow its oscillations, which can ultimately lead to structural failure. The severe consequences that fol
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Books on the topic "Subsonic flutter"

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United States. National Aeronautics and Space Administration., ed. Alleviation of whirl-flutter on a joined-wing tilt-rotor aircraft configuration using active controls. American Helicopter Society, 1991.

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2

Computational Investigation of Subsonic Torsional Airfoil Flutter. Storming Media, 1998.

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Book chapters on the topic "Subsonic flutter"

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Dinulović, Mirko. "Prediction of Subsonic Flutter Speeds for Composite Missile Fins Using Machine Learning." In Applied Artificial Intelligence 2: Medicine, Biology, Chemistry, Financial, Games, Engineering. Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-60840-7_14.

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Braune, Marc, and Stefan Wiggen. "Experimental Investigation of Flutter Mechanisms Depending on Sweep Under Subsonic Flow and Low Reynolds Numbers." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-64519-3_37.

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Höhn, Wolfgang, and Torsten H. Fransson. "Flutter Analysis of Two — Dimensional Viscous Subsonic and Transonic Flow in Turbomachines Using the Advection Upstream Splitting Method." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines. Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_13.

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Georgiou, Georgia, Hamed Haddad Khodaparast, and Jonathan E. Cooper. "Uncertainty Quantification of Aeroelastic Stability." In Advances in Computational Intelligence and Robotics. IGI Global, 2014. http://dx.doi.org/10.4018/978-1-4666-4991-0.ch016.

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The application of uncertainty analysis for the prediction of aeroelastic stability, using probabilistic and non-probabilistic methodologies, is considered in this chapter. Initially, a background to aeroelasticity and possible instabilities, in particular “flutter,” that can occur in aircraft is given along with the consideration of why Uncertainty Quantification (UQ) is becoming an important issue to the aerospace industry. The Polynomial Chaos Expansion method and the Fuzzy Analysis for UQ are then introduced and a range of different random and quasi-random sampling techniques as well as me
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Conference papers on the topic "Subsonic flutter"

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STRGANAC, THOMAS, MARIA MITCHUM, and DEAN MOOK. "The numerical simulation of subsonic flutter." In 19th AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1428.

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El-Aini, Y. M., H. R. Bankhead, and C. E. Meece. "Subsonic/Transonic Stall Flutter Investigation of an Advanced Low Pressure Compressor." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-90.

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The subsonic/transonic stall flutter characteristics of the Pratt &amp; Whitney PW1120 Low Pressure Compressor (LPC), recently have been defined through fan rig tests and a full-scale engine test. Flutter data analyses, based on both empirical and analytical methods, have shown excellent correlations between test results and predictions. While the LPC was demonstrated to be flutter-free over its entire flight envelope, the study indicates the need for continued research in transonic unsteady aerodynamics, particularly, the effects of passage shocks and large leading edge incidence.
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Meingast, Markus, Robert E. Kielb, and Jeffrey P. Thomas. "Preliminary Flutter Design Method for Supersonic Low Pressure Turbines." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59177.

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The “Tie-Dye” (TD) method is a well-known preliminary flutter design method for subsonic low pressure turbine (LPT) blades. In this paper, a study of 2D mode shape sensitivity using the TD-method for supersonic exit Mach numbers is presented. Using a harmonic balance CFD method, TD maps displaying the critical reduced frequency for a range of pitching axis locations were created. The TD method was run on two geometrically different blades. Subsonically, the characteristic appearance does not change much over airfoil types. An even lesser amount of morphing can be observed between the different
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Sawyer, Scott, and Sanford Fleeter. "Flutter stability of a detuned cascade in subsonic compressible flow." In 32nd Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-144.

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DURMUŞ, D., and M. KAYA. "Effects of Span Morphing on Flutter Characteristics of Subsonic Wing." In 14th WCCM-ECCOMAS Congress. CIMNE, 2021. http://dx.doi.org/10.23967/wccm-eccomas.2020.128.

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Kobayashi, Hiroshi. "Annular Cascade Study of Low Back-Pressure Supersonic Fan Blade Flutter." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-297.

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Low back-pressure supersonic fan blade flutter in the torsional mode was examined using a controlled-oscillating annular cascade test facility. Precise data of unsteady aerodynamic forces generated by shock wave movement due to blade oscillation and the previously measured data of chordwise distributions of unsteady aerodynamic forces acting, on an oscillating blade were joined, and then the nature of cascade flutter was evaluated. These unsteady aerodynamic forces were measured by direct and indirect pressure measuring methods. Our experiments covered a range of reduced frequencies based on a
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Benvenuto, Marcello, Andrea Silingardi, Pio Astrua, and Stefano Cecchi. "Sensitivity Analysis to Flutter for Front Stages Compressor Blades." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42588.

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Heavy duty gas turbine front stages compressor blades aero-elastic behavior is deeply analyzed and investigated by means of an uncoupled, non-linear and time-accurate CFD URANS solver. The travelling-wave approach and the energy method have been applied in order to assess the aerodynamic damping (in terms of logarithmic decrement) for each inter blade phase angle (IBPA) and thus to localize the flutter stability region. The work is mainly focused on a sensitivity analysis with respect to blade operating conditions, eigen-mode shapes and frequency in order to improve the understanding of flutte
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HENDERSON, GREGORY, and SANFORD FLEETER. "Aerodynamically forced response and flutter of structurally mistunedbladed disks in subsonic flow." In 30th Structures, Structural Dynamics and Materials Conference. American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-1387.

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Lasiecka, Irena, and Justin T. Webster. "Controlling flutter for nonlinear panels in subsonic flows via structural velocity feedback." In 2014 IEEE 53rd Annual Conference on Decision and Control (CDC). IEEE, 2014. http://dx.doi.org/10.1109/cdc.2014.7039443.

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Hashimoto, Atsushi, Yasuyuki Furuta, Naoto Yagi, and Yoshiaki Nakamura. "Experimental and Numerical Investigation of Delta Wing Flutter in Low Subsonic Flow." In 36th AIAA Fluid Dynamics Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-3215.

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