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Flutter Boundary Identification from Time-Domain Simulations Using the Matrix Pencil Method

2019; American Institute of Aeronautics and Astronautics; Volume: 57; Issue: 8 Linguagem: Inglês

10.2514/1.j058072

1533-385X

Jan F. Kiviaho, Kevin Jacobson, Graeme Kennedy,

Aerodynamics and Acoustics in Jet Flows

No AccessTechnical NotesFlutter Boundary Identification from Time-Domain Simulations Using the Matrix Pencil MethodJan F. Kiviaho, Kevin E. Jacobson and Graeme J. KennedyJan F. KiviahoGeorgia Institute of Technology, Atlanta, Georgia 30332, Kevin E. JacobsonGeorgia Institute of Technology, Atlanta, Georgia 30332 and Graeme J. KennedyGeorgia Institute of Technology, Atlanta, Georgia 30332Published Online:10 Jun 2019https://doi.org/10.2514/1.J058072SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Clark W. S. and Hall K. C., "A Time-Linearized Navier–Stokes Analysis of Stall Flutter," Journal of Turbomachinery, Vol. 122, No. 3, Feb. 1999, pp. 467–476. doi:https://doi.org/10.1115/1.1303073 CrossrefGoogle Scholar[2] Jonsson E., Riso C., Lupp C. A., Cesnik C. E. S., Martins J. R. R. A. and Epureanu B. 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Google Scholar[35] Bathe K.-J., Finite Element Procedures, 2nd ed., Prentice Hall, Upper Saddle River, NJ, 1996. Google Scholar Previous article FiguresReferencesRelatedDetailsCited byModel Parameter Estimation Method on Multichannel Structural Response from Turbulence Flutter TestInternational Journal of Aerospace Engineering, Vol. 2022Aerothermoelastic Analysis and Optimization of Stiffened Thin-Walled StructuresLenard J. Halim, Sejal Sahu, Graeme Kennedy and Marilyn J. Smith29 December 2021Multimodal Estimation of Sine Dwell Vibrational Responses from Aeroelastic Flutter Flight Tests1 November 2021 | Aerospace, Vol. 8, No. 11Dynamic instability analysis of aeroelastic systems with application to aircraft wingsPhysics of Fluids, Vol. 33, No. 9Multiscale Mesh Adaptation for Transonic Aeroelastic Flutter ProblemsKevin Jacobson, Bret Stanford, Jan F. Kiviaho, Thomas A. Ozoroski , Michael A. Park and Pawel Chwalowski28 July 2021A High-Fidelity Coupling Framework for Aerothermoelastic Analysis and Adjoint-Based Gradient EvaluationLiam J. Smith, Lenard J. Halim, Graeme Kennedy and Marilyn J. Smith4 January 2021 What's Popular Volume 57, Number 8August 2019Special Section on Sensitivity Analysis for Rotorcraft Optimization CrossmarkInformationCopyright © 2019 by Graeme J. Kennedy. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. TopicsAerodynamic PerformanceAerodynamicsAeroelasticityAeronautical EngineeringAeronauticsCFD CodesComputational Fluid DynamicsEquations of Fluid DynamicsFinite Difference MethodFlow RegimesFluid DynamicsNumerical Analysis KeywordsNACA 64A010Singular Value DecompositionAerodynamic SimulationStructural ModelingFUN3DAeroelastic ModelsDynamic PressureFrequency DomainAngle of AttackNewton's MethodAcknowledgmentsThe authors gratefully acknowledge the funding provided by NASA through the Transformative Tools and Technologies program with grant number NNX15AU22A with Technical Monitor Steve Massey. The authors specifically thank Jordan Trout for his assistance in running the final aeroelastic benchmark cases. Resources supporting this work were provided by the NASA High-End Computing (HEC) Program through the NASA Advanced Supercomputing (NAS) Division at Ames Research Center.PDF Received2 November 2018Accepted9 May 2019Published online10 June 2019