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Journal articles on the topic 'Subsonic flutter'

Author: Grafiati

Published: 4 June 2021

Last updated: 28 July 2025

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1

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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2

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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3

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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4

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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5

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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6

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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7

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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8

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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9

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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10

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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11

Zhang, Da Qian, Xiao Dong Tan, Zi Lei Zhang, and Xin Ping Fu. "Flutter Optimized Design for a Aircraft Horizontal Tail Base on Optimus Software." Applied Mechanics and Materials 684 (October 2014): 58–63. http://dx.doi.org/10.4028/www.scientific.net/amm.684.58.

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Based on the similarity theory, the horizontal tail scale model is designed and manufactured. Subsonic doublet lattice method is used to calculate unsteady aerodynamics, V-g method is used to solve the flutter determinant. Optimus software is used to optimize the thickness of the skin. The constraint condition is the frequency, MAC value and flexibility, and the objective function is flutter dynamic pressure. Flutter velocity of horizontal tail model optimized decreased 6%,and flutter frequency increased greatly. Horizontal tail scale model was test in wind tunnel. The finite element calculate

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12

Ma, Li, Minghui Yao, Wei Zhang, Kai Lou, Dongxing Cao, and Yan Niu. "A Novel Aerodynamic Force and Flutter of the High-Aspect-Ratio Cantilever Plate in Subsonic Flow." Shock and Vibration 2020 (June 19, 2020): 1–17. http://dx.doi.org/10.1155/2020/8841590.

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This paper focuses on the derivation of the aerodynamic force for the cantilever plate in subsonic flow. For the first time, a new analytical expression of the quasi-steady aerodynamic force related to the velocity and the deformation for the high-aspect-ratio cantilever plate in subsonic flow is derived by utilizing the subsonic thin airfoil theory and Kutta-Joukowski theory. Results show that aerodynamic force distribution obtained theoretically is consistent with that calculated by ANSYS FLUENT. Based on the first-order shear deformation and von Karman nonlinear geometric relationship, nonl

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13

Rahtika, I. Putu Gede Sopan, I. Made Suarta, I. Komang Rusmariadi, and Putu Wijaya Sunu. "Experimental Investigation on the Effect of Angles of Attack to the Flutter Speed of a Flat Plate in Axial Flow." Logic : Jurnal Rancang Bangun dan Teknologi 21, no. 2 (2021): 111–16. http://dx.doi.org/10.31940/logic.v21i2.2630.

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The application of flat plates to the field of wind harvesting requires a lot of research toward the understanding of the flutter behavior of the plates. There are shortages of articles that discuss the effect of varying the angles of attack to the flutter speed of a flat plate. This research aims to conduct a basic experimental research on the effect of relative position of a thin-flat plates to the direction of the air flow to its flutter speed. In this study, a thin-flat plate was placed in a subsonic wind tunnel to test its flutter speed. The position of the plate was varied in various ang

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14

Dinulović, Mirko, Mato Perić, Dragi Stamenković, Aleksandar Bengin, Vuk Adžić, and Marta Trninić. "Aeroelastic Behavior of 3D-Printed Tapered Polylactic Acid Plates Under Subsonic Flow Conditions." Materials 18, no. 5 (2025): 1127. https://doi.org/10.3390/ma18051127.

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This research investigates the aeroelastic stability of tapered polylactic acid (PLA) plates produced through fused deposition modeling (FDM) under low-Mach-number airflow conditions. While the static properties of 3D-printed structural components for drones, unmanned aerial vehicles (UAVs), and unmanned aircraft systems (UAS) have been thoroughly explored, their dynamic behavior, especially flutter, has been less studied. This study applies a binary flutter model to thin PLA plates, and the analytically predicted flutter speeds are compared with experimental data from wind-tunnel tests. The s

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15

Ali, Ahmed Abd Al-Hussain, and Mohammed Ismael Hamed. "The Effect of Laminated Layers on the Flutter Speed of Composite Wing." Journal of Engineering 18, no. 08 (2023): 924–34. http://dx.doi.org/10.31026/j.eng.2012.08.06.

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The paper presents an investigation to the flutter speed of composite wing for different ply orientation. Structurally the composite wing was idealized as a composite beam load carrying structure. Theodorsen’s expression was used to get the 2- dimension unsteady lifting force and pitching moment in the limit of incompressible flow and subsonic speed which were integrated over the wing span. A free vibration analysis was first carried out to get the natural frequencies and mode shapes .The velocity-damping (V-g) method was used to calculate the flutter speed and the flutter frequency. A wing of

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16

Dinulović, Mirko, Boško Rašuo, Ana Slavković, and Goran Zajić. "Flutter analysis of tapered composite fins: Analysis and experiment." FME Transactions 50, no. 3 (2022): 576–85. http://dx.doi.org/10.5937/fme2203576d.

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In the present work, the aeroelastic stability of tapered composite plates is investigated. Existing flutter models, based on the typical section approach, are reviewed for quasi-steady and unsteady low Mach number axial flows and modified for the thin composite tapered plates. The numerical approach, based on panel vortex methods for flutter analysis, is presented, and results are compared to typical section flutter methods for the tapered composite fins. Experimental work is performed in the subsonic wind tunnel at flow speeds of 20 - 30 m/s range. Good agreement between experimental, analyt

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17

Sanders, A. J., K. K. Hassan, and D. C. Rabe. "Experimental and Numerical Study of Stall Flutter in a Transonic Low-Aspect Ratio Fan Blisk." Journal of Turbomachinery 126, no. 1 (2004): 166–74. http://dx.doi.org/10.1115/1.1645532.

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Experiments are performed on a modern design transonic shroudless low-aspect ratio fan blisk that experienced both subsonic/transonic and supersonic stall-side flutter. High-response flush mounted miniature pressure transducers are utilized to measure the unsteady aerodynamic loading distribution in the tip region of the fan for both flutter regimes, with strain gages utilized to measure the vibratory response at incipient and deep flutter operating conditions. Numerical simulations are performed and compared with the benchmark data using an unsteady three-dimensional nonlinear viscous computa

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18

Berci, Marco, and Francesco Torrigiani. "Multifidelity Sensitivity Study of Subsonic Wing Flutter for Hybrid Approaches in Aircraft Multidisciplinary Design and Optimisation." Aerospace 7, no. 11 (2020): 161. http://dx.doi.org/10.3390/aerospace7110161.

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A comparative sensitivity study for the flutter instability of aircraft wings in subsonic flow is presented, using analytical models and numerical tools with different multidisciplinary approaches. The analyses build on previous elegant works and encompass parametric variations of aero-structural properties, quantifying their effect on the aeroelastic stability boundary. Differences in the multifidelity results are critically assessed from both theoretical and computational perspectives, in view of possible practical applications within airplane preliminary design and optimisation. A robust hy

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19

Elahi, Hassan, Marco Eugeni, Federico Fune, et al. "Performance Evaluation of a Piezoelectric Energy Harvester Based on Flag-Flutter." Micromachines 11, no. 10 (2020): 933. http://dx.doi.org/10.3390/mi11100933.

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In the last few decades, piezoelectric (PZT) materials have played a vital role in the aerospace industry because of their energy harvesting capability. PZT energy harvesters (PEH) absorb the energy from an operational environment and can transform it into useful energy to drive nano/micro-electronic components. In this research work, a PEH based on the flag-flutter mechanism is presented. This mechanism is based on fluid-structure interaction (FSI). The flag is subjected to the axial airflow in the subsonic wind tunnel. The performance evaluation of the harvester and aeroelastic analysis is i

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20

Logunov, Boris A., and Ilya A. Kharin. "Improving the Efficiency of Testing Aircraft Models for Flutter Using Measurement and Information Systems in a Subsonic Wind Tunnel." Vestnik MEI, no. 5 (2021): 103–7. http://dx.doi.org/10.24160/1993-6982-2021-5-103-107.

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The technology of testing dynamically and structurally similar aircraft models for flutter in subsonic wind tunnels using information and measurement systems (IMS) is based on collection and processing of experimental data obtained in subcritical modes. The data received feature a significant scatter, in view of which the critical flutter speed is determined with acceptable accuracy only after its statistical post-processing. In view of the need to study a number of model versions during the flutter tests, the technology involved significant time spent for wind tunnel air flow startups and for

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21

Bakhle, Milind A., T. S. R. Reddy, and Theo G. Keith. "Subsonic/Transonic Cascade Flutter Using a Full-Potential Solver." AIAA Journal 31, no. 7 (1993): 1347–49. http://dx.doi.org/10.2514/3.49072.

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22

Lin, Kuo-Juin, Pong-Jeu Lu, and Jiann-Quo Tarn. "Flutter analysis of cantilever composite plates in subsonic flow." AIAA Journal 27, no. 8 (1989): 1102–9. http://dx.doi.org/10.2514/3.10228.

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23

Long, Wei, Yan Liu, and Jia Ming Cao. "Wing Flutter Analysis Parameters during Flight." Applied Mechanics and Materials 722 (December 2014): 93–96. http://dx.doi.org/10.4028/www.scientific.net/amm.722.93.

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This paper adapts finite element analysis of dynamic structure to analysis airfoil based on the phenomenon that torsion coupling may happen to airfoil during flying,, which verifies flutter mechanism of swing under subsonic and transonic condition. Modal frequency error can be changed into stiffness error by error analysis. The errors of bending and torsion frequency are verified by adjusting stiffness and mass distribution. Meanwhile the concept of modal strain energy is introduced to character and identify different positions and structures of damages.

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24

Vinayagamurthy, G., K. M. Parammasivam, and S. Nadaraja Pillai. "Flutter Analysis of Wing, Booster Fin and Vertical Tail." Applied Mechanics and Materials 110-116 (October 2011): 3500–3505. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.3500.

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Aerospace vehicles are subjected to various types of severe environmental loads. The basic design criterion includes the minimum weight configuration that results in very flexible structures, which leads to various types of structural interaction problems like flutter, divergence etc. Hence every aerospace vehicle should be analysed for its aeroelastic instabilities. In the present work the flutter analysis of a typical space vehicle was carried out in substructure level with the interface fixed condition. The doublet lattice, zona51 and piston theories are used in the unsteady aerodynamic cal

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25

Muñoz, Álvaro, and Pablo García-Fogeda. "Active Flutter Suppression of a Wing Section in a Compressible Flow." Aerospace 9, no. 12 (2022): 804. http://dx.doi.org/10.3390/aerospace9120804.

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In this paper, a unified method for the computation of the unsteady aerodynamic forces in the Laplace domain for a wing section in subsonic, sonic and supersonic potential flows is presented. The subsonic solution is a new development based on the pressure mode method. The unsteady aerodynamic forces are evaluated in the Laplace domain by an efficient method for computing the kernel. The sonic potential flow solution is an extension of the solution for the frequency domain to the Laplace domain. Analytical expressions for the unsteady pressure coefficient and the unsteady aerodynamic forces in

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26

Alizadeh, A., Z. Ebrahimi, A. Mazidi, and S. Ahmad Fazelzadeh. "Experimental Nonlinear Flutter Analysis of a Cantilever Wing/Store." International Journal of Structural Stability and Dynamics 20, no. 07 (2020): 2050082. http://dx.doi.org/10.1142/s0219455420500820.

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This paper studies experimentally the nonlinear aeroelastic and flutter behavior of a cantilever plate wing with an external store. The wing model that is constructed from plexiglass sheet is designed and tested in a closed-circuit subsonic wind tunnel. To deal with the structural nonlinearities of the model, various analysis tools such as time history plots, phase-plane projections and Fast Fourier Transform (FFT) have been used for detecting the critical and post-critical behaviors of the structure. The results show that flutter takes place by the coupling between the torsional and bending m

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27

Wasmi, Hatem Rahim, Ali Abdul Mohsin Hasan, and Waleed Jasim Mhaimeed. "Aeroelastic Flutter of Subsonic Aircraft Wing Section with Control Surface." Journal of Engineering 21, no. 12 (2015): 104–23. http://dx.doi.org/10.31026/j.eng.2015.12.07.

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Aeroelastic flutter in aircraft mechanisms is unavoidable, essentially in the wing and control surface. In this work a three degree-of-freedom aeroelastic wing section with trailing edge flap is modeled numerically and theoretically. FLUENT code based on the steady finite volume is used for the prediction of the steady aerodynamic characteristics (lift, drag, pitching moment, velocity, and pressure distribution) as well as the Duhamel formulation is used to model the aerodynamic loads theoretically. The system response (pitch, flap pitch and plunge) was determined by integration the governing

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28

Vedeneev, Vasily. "Interaction of panel flutter with inviscid boundary layer instability in supersonic flow." Journal of Fluid Mechanics 736 (November 4, 2013): 216–49. http://dx.doi.org/10.1017/jfm.2013.522.

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AbstractWe investigate the stability of an elastic plate in supersonic gas flow. This problem has been studied in many papers regarding panel flutter, where uniform flow is usually considered. In this paper, we take the boundary layer on the plate into account and investigate its influence on plate stability. Three problem formulations are studied. First, we investigate the stability of travelling waves in an infinite-length plate. Second, the nature of the instability (absolute or convective instability) is examined. Finally, by using solutions of the first two problems, instability of a long

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29

Sawyer, Scott, and Sanford Fleeter. "Flutter stability of a detuned cascade in subsonic compressible flow." Journal of Propulsion and Power 11, no. 5 (1995): 923–30. http://dx.doi.org/10.2514/3.23918.

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30

Balakrishnan, A. V., and K. W. Iliff. "Continuum Aeroelastic Model for Inviscid Subsonic Bending-Torsion Wing Flutter." Journal of Aerospace Engineering 20, no. 3 (2007): 152–64. http://dx.doi.org/10.1061/(asce)0893-1321(2007)20:3(152).

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31

Yaman, Kemal, and Mevlüt Burak Dalmış. "Corrigendum to “Subsonic Flutter of Cantilever Rectangular PC Plate Structure”." International Journal of Aerospace Engineering 2018 (July 24, 2018): 1. http://dx.doi.org/10.1155/2018/5808621.

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32

Sláma, Václav, Bartoloměj Rudas, Petr Eret, et al. "EXPERIMENTAL AND NUMERICAL STUDY OF CONTROLLED FLUTTER TESTING IN A LINEAR TURBINE BLADE CASCADE." Acta Polytechnica CTU Proceedings 20 (December 31, 2018): 98–107. http://dx.doi.org/10.14311/app.2018.20.0098.

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In this paper, experimental testing of flutter and numerical simulations using a commercial code ANSYS CFX and an in-house code TRAF are performed on an oscillating linear cascade of turbine blades installed in a subsonic test rig. Bending and torsional motions of the blades are investigated in a travelling wave mode approach. In each numerical approach, a rig geometry model with a different level of complexity is used. Good agreement between the numerical simulations and experiments is achieved using both approaches and benefits and drawbacks of each technique are commented in this paper. It

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33

Зиньковский, Анатолий Павлович, Анатолий Леонидович Стельмах та Сергей Николаевич Кабанник. "РЕЗУЛЬТАТЫ ОЦЕНКИ ДИНАМИЧЕСКОЙ УСТОЙЧИВОСТИ К ДОЗВУКОВОМУ ФЛАТТЕРУ ЛОПАТОЧНЫХ ВЕНЦОВ КОМПРЕССОРОВ НЕКОТОРЫХ АВИАЦИОННЫХ ГАЗОТУРБИННЫХ ДВИГАТЕЛЕЙ". Aerospace technic and technology, № 8 (31 серпня 2019): 78–84. http://dx.doi.org/10.32620/aktt.2019.8.12.

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The paper outlines the results of the investigation on the verification of the express method of prediction of dynamic stability for subsonic flutter using the blade assemblies of individual stages of the compressor of some types of aircraft gas-turbine engines at different modes of their operation. The paper gives a brief overview of the basic concepts of the developed express estimation method, possibilities of the determination of the stability limit for the blade assemblies for a subsonic flutter, as well as the results of the assessment of the dynamic stability of the compressor stages of

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34

Schäfer, Dominik. "Influence of Fluid Viscosity and Compressibility on Nonlinearities in Generalized Aerodynamic Forces for T-Tail Flutter." Aerospace 9, no. 5 (2022): 256. http://dx.doi.org/10.3390/aerospace9050256.

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The numerical assessment of T-tail flutter requires a nonlinear description of the structural deformations when the unsteady aerodynamic forces comprise terms from lifting surface roll motion. For linear flutter, a linear deformation description of the vertical tail plane (VTP) out-of-plane bending results in a spurious stiffening proportional to the steady lift forces, which is corrected by incorporating second-order deformation terms in the equations of motion. While the effect of these nonlinear deformation components on the stiffness of the VTP out-of-plane bending mode shape is known from

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35

Vladimirescu, Tudor, Ion Fuiorea, and Tudor Vladimirescu-jr. "IAR-99 HAWK Flutter Model Studies with External Stores." Science, Technology & Public Policy 9, no. 1 (2025): 1–13. https://doi.org/10.11648/j.stpp.20250901.11.

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The new Finite Elements Model (FEM) allows the visualization of the results and the study of the behavior of the structure at the local level (frames; lises; spars; frame-body, shell-body and longeron-body interaction) in the case of global dynamical phenomena. After creating FEM of the aircraft IAR-99 HAWK in the empty equipped configuration using special elements, the team decided to extend the study of flutter to aircraft in different external stores configurations. The results of the theoretical free-free vibrations obtained for the IAR-99 HAWK in different external stores configurations a

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36

Chajec, Wojciech. "Comparison of flutter calculation methods based on ground vibration test result." Aircraft Engineering and Aerospace Technology 91, no. 3 (2019): 466–76. http://dx.doi.org/10.1108/aeat-03-2018-0102.

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PurposeA low-cost but credible method of low-subsonic flutter analysis based on ground vibration test (GVT) results is presented. The purpose of this paper is a comparison of two methods of immediate flutter problem solution: JG2 – low cost software based on the strip theory in aerodynamics (STA) and V-g method of the flutter problem solution and ZAERO I commercial software with doublet lattice method (DLM) aerodynamic model and G method of the flutter problem solution. In both cases, the same sets of measured normal modes are used. Design/methodology/approachBefore flutter computation, resona

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37

Lasiecka, Irena, and Justin Webster. "Eliminating flutter for clamped von Karman plates immersed in subsonic flows." Communications on Pure & Applied Analysis 13, no. 5 (2014): 1935–69. http://dx.doi.org/10.3934/cpaa.2014.13.1935.

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38

Chuban, Vitalii Dmitrievich. "PANEL FLUTTER OF PLATE UNDER SUBSONIC FLOW IN TWO-DIMENSIONAL APPROACH." TsAGI Science Journal 51, no. 1 (2020): 85–98. http://dx.doi.org/10.1615/tsagiscij.2020034274.

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39

ISOGAI, Koji. "Numerical Simulation of T-Tail Flutter in Subsonic and Transonic Flows." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 67, no. 5 (2024): 260–73. http://dx.doi.org/10.2322/tjsass.67.260.

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40

Majid, Dayang Laila Abang Haji Abdul, and ShahNor Basri. "LCO flutter of cantilevered woven glass/epoxy laminate in subsonic flow." Acta Mechanica Sinica 24, no. 1 (2008): 107–10. http://dx.doi.org/10.1007/s10409-007-0117-y.

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41

Afonso, F., J. Vale, É. Oliveira, F. Lau, and A. Suleman. "Non-linear aeroelastic response of high aspect-ratio wings in the frequency domain." Aeronautical Journal 121, no. 1240 (2017): 858–76. http://dx.doi.org/10.1017/aer.2017.29.

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ABSTRACTA current trend in the aeronautic industry is to increase the wing aspect ratio to enhance aerodynamic efficiency by reducing the induced drag and thus reduce fuel consumption. Despite the associated benefits of a large aspect ratio, such as higher lift-to-drag ratios and range, commercial aircraft usually have a relatively low aspect ratio. This is partially explained by the fact that the wing becomes more flexible with increasing aspect ratio and thus more prone to large deflections, which can cause aeroelastic instability problems such as flutter. In this work, an aeroelastic study

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Shubov, Marianna A., Stephen Wineberg, and Robert Holt. "Numerical Investigation of Aeroelastic Mode Distribution for Aircraft Wing Model in Subsonic Air Flow." Mathematical Problems in Engineering 2010 (2010): 1–23. http://dx.doi.org/10.1155/2010/879519.

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In this paper, the numerical results on two problems originated in aircraft wing modeling have been presented.The first problemis concerned with the approximation to the set of the aeroelastic modes, which are the eigenvalues of a certain boundary-value problem. The affirmative answer is given to the following question: can the leading asymptotical terms in the analytical formulas be used as reasonably accurate description of the aeroelastic modes? The positive answer means that these leading terms can be used by engineers for practical calculations.The second problemis concerned with the flut

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Ayer, T. C., and J. M. Verdon. "Validation of a Nonlinear Unsteady Aerodynamic Simulator for Vibrating Blade Rows." Journal of Turbomachinery 120, no. 1 (1998): 112–21. http://dx.doi.org/10.1115/1.2841372.

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A time-accurate Euler/Navier–Stokes analysis is applied to predict unsteady subsonic and transonic flows through a vibrating cascade. The intent is to validate this nonlinear analysis along with an existing linearized inviscid analysis via result comparisons for unsteady flows that are representative of those associated with blade flutter. The time-accurate analysis has also been applied to determine the relative importance of nonlinear and viscous effects on blade response. The subsonic results reveal a close agreement between inviscid and viscous unsteady blade loadings. Also, the unsteady s

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Guo, S. J., J. R. Bannerjee, and C. W. Cheung. "The effect of laminate lay-up on the flutter speed of composite wings." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 217, no. 3 (2003): 115–22. http://dx.doi.org/10.1243/095441003322297225.

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This paper presents an analytical study on optimization of a laminated composite wing structure for achieving a maximum flutter speed and a minimum weight without strength penalty. The investigation is carried out within the range of incompressible airflow and subsonic speed. In the first stage of the optimization, attention has been paid mainly to the effect on flutter speed of the bending, torsion and, more importantly, the bending-torsional coupling rigidity, which is usually associated with asymmetric laminate lay-up. The study has shown that the torsional rigidity plays a dominant role, w

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URSU, Ioan, Adrian TOADER, Daniela ENCIU, and George TECUCEANU. "Active robust control for wing vibrations attenuation." INCAS BULLETIN 14, no. 1 (2022): 209–24. http://dx.doi.org/10.13111/2066-8201.2022.14.1.17.

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In this paper a flexible smart wing is presented. The aileron wing with aileron was tested in the INCAS Subsonic Wind Tunnel with the aim of flutter mitigation and vibrations attenuation. The work takes over some of the results of the active anti-flutter control tests performed in the wind tunnel based on the receptance method. More specifically, the mathematical models in the time domain, necessary for the synthesis of control laws, are obtained from experimentally identified transfer functions. The main part of the paper presents the synthesis and analysis of the robustness of the control la

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Pátý, Marek, and Jan Halama. "Boundary conditions in flutter simulations of subsonic, transonic and supersonic blade cascades." Journal of Fluids and Structures 130 (November 2024): 104189. http://dx.doi.org/10.1016/j.jfluidstructs.2024.104189.

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Balakrishnan, A. V., Amjad M. Tuffaha, Iylene Patino, and Oleg Melnikov. "Flutter analysis of an articulated high aspect ratio wing in subsonic airflow." Journal of the Franklin Institute 351, no. 8 (2014): 4230–50. http://dx.doi.org/10.1016/j.jfranklin.2014.04.010.

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Li, Peng, Yiren Yang, and Li Lu. "Nonlinear flutter behavior of a plate with motion constraints in subsonic flow." Meccanica 49, no. 12 (2014): 2797–815. http://dx.doi.org/10.1007/s11012-014-0041-8.

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Chen, Tao, Min Xu, Dan Xie, and Xiaomin An. "Post-flutter response of a flexible cantilever plate in low subsonic flows." International Journal of Non-Linear Mechanics 91 (May 2017): 113–27. http://dx.doi.org/10.1016/j.ijnonlinmec.2017.02.016.

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Eret, Petr, Volodymyr Tsymbalyuk, and Markus Eckert. "Flutter Measurement of a Linear Turbine Blade Cascade with an Angular Position Deviation of One Blade." Strojnícky časopis - Journal of Mechanical Engineering 73, no. 2 (2023): 15–32. http://dx.doi.org/10.2478/scjme-2023-0019.

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Abstract Experimental flutter testing of high-aspect ratio rotor blades is a mainstay of turbomachinery research. However, rotor blades are never identical, and geometrical errors between actual and nominal geometries exist due to limited machining precision or assembly imperfection. The paper presents the initial phase of the controlled flutter research of a linear turbine blade cascade with a geometric deviation in one blade position. A subsonic wind tunnel with four flexibly mounted blades in an otherwise rigid blade cascade is employed at one angle of incidence and three low reduced freque

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