Nonlinear Oscillations of a Fluttering Panel in a Transonic Airstream.

Abstract

A flutter analysis has been conducted on a simply supported panel to demonstrate the successful combining of the panel (Von Karman) large deflection equations with a linear aerodynamic (Piston) theory for determining the panel response. The panel response was determined by coupling a Galerkin modal representation with a numerical time integration scheme. The time integration scheme was also successfully used to obtain the linear structural (small-deflection) response to a nonlinear aerodynamic pressure. Because the representation of the nonlinear panel response by a linear superposition of linear mode shapes is very questionable, the Von Karman large deflection equations were replaced by a large deflection finite-element representation. The nonlinear panel response of the finite-element model was obtained using Piston theory aerodynamics and it is recommended that the finite-element response be determined for a nonlinear aerodynamic pressure.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1983
Accession Number
ADA133918

Entities

People

  • Franklin E. Eastep

Organizations

  • University of Dayton

Tags

Communities of Interest

  • C4I
  • Cyber
  • Space

DTIC Thesaurus Topics

  • Aerodynamic Loading
  • Air Force
  • Computational Fluid Dynamics
  • Computational Science
  • Computer Programs
  • Differential Equations
  • Dynamic Loads
  • Dynamic Pressure
  • Dynamic Response
  • Equations
  • Fluid Dynamics
  • Frequency
  • Mach Number
  • Resonant Frequency
  • Shock Waves
  • Static Loads
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Structural Dynamics.