Accession Number : AD0824482


Title :   THE RESPONSE OF SIMPLE PANELS TO TURBULENT BOUNDARY LAYER EXCITATION


Descriptive Note : Final scientific rept. Nov 1963-Nov 1966


Corporate Author : SOUTHAMPTON UNIV (UNITED KINGDOM) INSTOF SOUND AND VIBRATION RESEARCH


Personal Author(s) : Wilby, John F


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/824482.pdf


Report Date : Oct 1967


Pagination or Media Count : 355


Abstract : The response of a series of panels to turbulent boundary layer excitation was measured for flow velocities of 329 ft./sec. and 540 ft./sec., and boundary layer thicknesses in the range 0.4 inch to 1.4 inches. The effects of boundary layer thickness, pressure field convection direction, panel aspect ratio and static pressure differential are well predicted. The effect of flow velocity is not predicted accurately, the theory over-estimating the effect near coincidence and under-estimating the effect elsewhere. The boundary layer thickness affects the panel vibration mainly through the pressure spectrum. Static pressure affects the vibration mainly through the change in stiffness. Random techniques are used to measure panel damping in the presence of an airflow and the results show an increase in damping due to the flow. The increase is small in general.


Descriptors :   *PANELS , *TURBULENT BOUNDARY LAYER , THICKNESS , RESPONSE , AIRCRAFT PANELS , UNITED KINGDOM , FLEXIBLE STRUCTURES , FLUTTER , DAMPING , VIBRATION


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE