TECHNICAL NOTE - PRELIMINARY WORK FOR MODELING THE PROPELLERS OF AN AIRCRAFT AS A NOISE SOURCE IN AN ACOUSTIC BOUNDARY-ELEMENT ANALYSIS

An algorithm for generating appropriate velocity boundary conditions f or an acoustic boundary element analysis from the kinematics of an ope rating propeller is presented. It constitutes the initial phase of int egrating sophisticated rotorcraft models into a conventional boundary element analysis. Currently, the pressure field is computed by a linea r approximation. An initial validation of the developed process was pe rformed by comparing numerical results to test data for the external a coustic pressure on the surface of a tilt-rotor aircraft for one fligh t condition. (C) 1998 Institute of Noise Control Engineering.