Unsteady compressible boundary element calculations of parallel blade-vortex interaction

A method for calculating parallel blade vortex interaction (BVI) has been d eveloped. The technique is based on the application of a three dimensional aeroacoustic boundary element formulation using Analytical/Numerical Matchi ng in conjunction with a recently developed viscous core trailing vortex ro ll-up model. Computational parameters were chosen to col respond with an ex perimental investigation conducted at NASA limes Research Center modeling p arallel BVI between a model rotor and an independently generated trailing v ortex. Calculations include rotor blade chordwise pressure distributions, b lade surface pressure time histories, and both near- and far-field radiated acoustic pressure time histories. Comparisons with experimental data demon strate the feasability of applying linear theory to the study of BVI.