Unsteady compressible boundary element calculations of parallel blade-vortex interaction

摘要

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 Analysis/Numerical Matching in conjunction with an recently developed viscous core trailing vortex roll-up model. Computational parameters were chosen to correspond with an experimental investigation conducted at NASA Amess Research Center modeling parallel BVI between a model rotor and an independently generated trailing vortex.