A FINITE ELEMENT ANALYSIS OF SIMPLE PANEL RESPONSE TO TURBULENT BOUNDARY LAYERS.
Abstract
Finite element matrix methods are shown to be useful in computing random response of elastic structure to stationary random loads which have random dependence on both space and time. A method is developed to determine the force cross power spectral density of subsonic attached turbulent boundary layers acting on structures with finite element idealization. These methods are demonstrated by comparison of calculated random response of a simple clamped panel (calculated on a FORTRAN IV computer program) with measurements taken in a boundary layer facility. The comparisons include deflection power spectral density and mean square displacement. Adequate damping representation is critical for good calculation of response values. Maximum deflection increases from modal coupling varied from zero to 6 percent. The attached boundary layer loading function appears adequate. The methods are useful in calculating random response of elastic structure to a wide range of stationary random loads. The greatest advantage of finite element methods is their flexibility, allowing accurate descriptions of complex structures that represent real aircraft sections.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1967
- Accession Number
- AD0825514
Entities
People
- Dennis R. Lagerquist
- Loyd D. Jacobs
Organizations
- Boeing