An algorithm for generating appropriate velocity boundary conditions for an acoustic boundary element analysis from the kinematics of an operating propeller is presented. It constitutes the initial phase of integrating sophisticated rotorcraft models into a conventional boundary element analysis. Currently, the pressure field is computed by a linear approximation. An initial validation of the developed process was performed by comparing numerical results to test data for the external acoustic pressure on the surface of a tilt-rotor aircraft for one flight condition.
Technical note: preliminary work for modeling the propellers of an aircraft as a noise source in an acoustic boundary element analysis
Noise Control Engineering Journal ; 46 , 3 ; 132-136
1998
5 Seiten, 29 Quellen
Aufsatz (Zeitschrift)
Englisch
SAE Technical Papers | 1929
|Engineering Index Backfile | 1929
|Engineering Index Backfile | 1929
|NTIS | 1940