Accession Number:

ADA133918

Title:

Nonlinear Oscillations of a Fluttering Panel in a Transonic Airstream.

Descriptive Note:

Final rept. 1 May 81-1 May 82,

Corporate Author:

DAYTON UNIV OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1983-04-01

Pagination or Media Count:

110.0

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.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE