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) : Eastep,Franklin E
PDF Url : ADA133918
Report Date : Apr 1983
Pagination or Media Count : 110
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.
Descriptors : *Aeroelasticity, *Flutter, *Panels, *Transonic flow, *Aerodynamics, Oscillation, Nonlinear systems, Deflection, Equations, Theory, Structural response, Numerical analysis, Time, Integration, Aerodynamic loading, Pressure, Pitch(Inclination), Airfoils, Lift, Finite element analysis, Mathematical models, Computer programs
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE