Unsteady compressible boundary element calculations of parallel blade-vortex interaction
© 1998 by The Boeing Company. Published by the American Institute of Aeronautics and Astronautics, Inc. A novel 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 new viscous core trailing vortex roll-up model. Run parameters were chosen to correspond with a comprehensive parallel BVI experimental study conducted at NASA. Calculations include both near- and far-field radiated acoustic pressure, blade surface pressure time histories and chordwise pressure distributions. Comparisons with experimental data demonstrate the feasability of applying linear theory to the study of BVI. The results presented have implications on the understanding of the essential physics of the BVI problem.
