RESPONSE OF AN ACOUSTICALLY LOADED PANEL EXCITED BY SUPERSONICALLY CONVECTED TURBULENCE
Abstract
Measurements were made of the wall pressure fluctuation and the response of the panel structure. The plate is excited by a boundary layer (M=3. 03) and shock impingement (15 deg angle) the flow downstream of the shock is separated. The wall pressure fluctuations and panel displacement are notably greater than the case without the shock present. The response of a plate clamped in a baffle is determined. The plate is coupled acoustically to a uniformly moving fluid. The boundary-layer exciting the plate does not interact with the acoustic field and is furthermore taken to be spatially uncorrelated. Finally, the radiation is determined over the solid angle of the Mach cone. The response is derived using finite Fourier transforms and then solving the resulting algebraic equation by expressing the solution expanded in a complete set of functions, a process which leads to an infinite set of linear equations. The right-hand side of this system of equations is a stochastic variable so that performing an ensemble average the resulting equation is solved for the covariance matrix which is subsequently diagonalized to yield the power spectral density in the statistically independent states (degrees of freedom).
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1970
- Accession Number
- AD0707258
Entities
People
- L. Maestrello
- T. L. Linden
Organizations
- Boeing