Experimental data are presented to show evidence of chaotic response of two adjacent aircraft panels forced by a turbulent boundary layer and pure tone sound. The experiments are a simulation of boundary-layer and fan noise loads on a fuselage sidewall with Reynolds number per meter d 2.85 x 105. The response of the panels is purely random and assumed linear when forced by the turbulent boundary-layer flow and clearly becomes nonlinear with the appearance of the interspersed periodic to chaotic motion when forced by the boundary layer with superimposed pure tone sound. The initial periodic response of two tori of two commensurate frequencies changes with an increase in pure tone sound level. The response or period-doubling bifurcations then makes a transition to chaos, which alternates with quasiperiodic response as the wave loses the spatial homogeneity. The objective is to demonstrate the existence of strong nonlinear effects on the structure response, which is not yet well understood.
Chaotic response of panel vibrations forced by turbulent boundary layer and sound
Chaotische Schwingungen der Flugzeugverkleidung, verursacht durch die turbulente Grenzschicht und die Schallemissionen des Triebwerks
AIAA Journal ; 37 , 3 ; 289-295
1999
7 Seiten, 7 Bilder, 1 Tabelle, 33 Quellen
Article (Journal)
English
FLUID DYNAMICS - Chaotic Response of Panel Vibrations Forced by Turbulent Boundary Layer and Sound
Online Contents | 1999
|Nonlinear Panel Response from a Turbulent Boundary Layer
AIAA | 1972
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