A WAVENUMBER APPROACH TO MODELLING THE RESPONSE OF A RANDOMLY EXCITED PANEL, PART II: APPLICATION TO AIRCRAFT PANELS EXCITED BY A TURBULENT BOUNDARY LAYER

Part I of this paper has shown the suitability of wavenumber–frequency approach in the calculation of the vibro-acoustic response of a thin baffled plate to a large class of random excitations. Part II describes the application of this formulation to the prediction of the vibration and the acoustic radiation of an aircraft fuselage panel exposed to boundary layer turbulence. rst section briefly describes the modelling of the wall-pressure fluctuations and justifies as to why a Corcos-like model for the wall-pressure field is suitable for high subsonic flow applications. In the next sections, several parametric studies are presented. These are first used to verify the validity of the hypothesis underlying our simplified model. Then we examine the influence of the main physical parameters on the vibro-acoustic response of the system. Finally, the predictions of our model are compared with some previously reported experimental measurements taken on a panel excited by a turbulent boundary layer.