Unsteady compressible boundary element calculations of parallel blade-vortex interaction

Abstract

A method for calculating parallel blade vortex interaction (BVI) has been developed. The technique is based on the application of a three-dimensional aeroacoustic boundary element formulation using Analytical/Numerical Matching in conjunction with a recently developed viscous core trailing vortex roll-up model. Computational parameters were chosen to correspond with an experimental investigation conducted at NASA Ames Research Center modeling parallel BVI between a model rotor and an independently generated trailing vortex. Calculations include rotor blade chordwise pressure distributions, blade surface pressure time histories, and both near- and far-field radiated acoustic pressure time histories. Comparisons with experimental data demonstrate the feasability of applying linear theory to the study of BVI.

DOI
10.4050/JAHS.44.302
Year