Computation of Three-Dimensional Nonlinear Panel Flutter
Publication: Journal of Aerospace Engineering
Volume 16, Issue 4
Abstract
A recently developed three-dimensional viscous aeroelastic solver is applied to the solution of nonlinear panel flutter. The solution scheme implicitly couples a well validated Navier-Stokes code with a finite-difference procedure for the Von Karman plate equations by employing a subiteration strategy. Both low supersonic, and subsonic, cases are computed. For the supersonic case, the presence of either a laminar or turbulent boundary layer delays the onset of flutter, with higher flutter dynamic pressures resulting for thicker boundary layers. This effect is much less pronounced when the boundary layers are turbulent. In the subsonic case multiple solutions are obtained. The downwardly divergent solution displays a very complex interaction between the laminar boundary layer and the flexible panel that results in significant acoustic radiation from the vibrating panel.
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Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 16 • Issue 4 • October 2003
Pages: 155 - 166
Copyright
Copyright © 2003 American Society of Civil Engineers.
History
Received: Jun 25, 2002
Accepted: Mar 25, 2003
Published online: Sep 15, 2003
Published in print: Oct 2003
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