Linear and Nonlinear Flutter of Supersonic Panels of Various Shapes
Publication: Journal of Engineering Mechanics
Volume 147, Issue 3
Abstract
A fluid-structure model based on nonlinear Mindlin-Reissner plate theory and linearized piston theory is used to study the aeroelastic flutter of panels of arbitrary planforms at supersonic Mach numbers. A finite-element procedure is used to reduce the continuous system to a fully coupled finite-dimension flow-structure system, which is solved in the time domain using the Newmark method. Panels with hinged or clamped boundary conditions and surrounded by a rigid baffle are considered. Critical velocity and frequency at onset of flutter are determined for triangular, square, circular, semi-circular, elliptic, and hexagonal forms. Limit cycle oscillations (LCOs) amplitudes are computed for a range of aerodynamic loading for all panels. Based on the finite-element data, scaling laws in the form of simple algebraic formulas are proposed that enable prediction of modal coalescence flutter velocity, frequency, and LCO amplitudes in terms of geometric and materials properties of panels. Such scaling laws are helpful in the preliminary design and optimization of supersonic panels or developing reduced-order models of supersonic panel flutter.
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Data Availability Statement
A MATLAB code for computing limit cycle oscillations amplitudes for square and circular panels is available from the corresponding author upon reasonable request.
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Published In
Journal of Engineering Mechanics
Volume 147 • Issue 3 • March 2021
Copyright
© 2020 American Society of Civil Engineers.
History
Received: Jul 7, 2020
Accepted: Nov 3, 2020
Published online: Dec 31, 2020
Published in print: Mar 1, 2021
Discussion open until: May 31, 2021
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