Large Eddy simulation of parallel blade-vortex interaction
Abstract
Helicopter Blade-Vortex Interaction (BVI) generally occurs under certain conditions of powered descent or during extreme maneuvering. The vibration and acoustic problems associated with the interaction of rotor tip vortices and the following blades is a major aerodynamic concern for the helicopter community. Numerous experimental and computational studies have been done over the last two decades in order to gain a better understanding of the physical mechanisms involved in BVI. The most severe interaction, in terms of generated noise, happens when the vortex filament is parallel to the blade, thus affecting a great portion of it. The majority of the previous numerical studies of parallel BVI fall within a potential flow framework. Some Navier-Stokes approaches using dissipative numerical methods and RANS-type turbulence models have also been attempted, but with limited success. The current investigation makes use of an incompressible, non-dissipative, kinetic energy conserving collocated mesh scheme in conjunction with a dynamic subgrid-scale model. The concentrated tip vortex is not attenuated as it is convected downstream and over a NACA-0012 airfoil. The lift, drag, moment and pressure coefficients induced by the passage of the vortex are monitored in time and compared with experimental data.
- Publication:
-
APS Division of Fluid Dynamics Meeting Abstracts
- Pub Date:
- November 2002
- Bibcode:
- 2002APS..DFD.MK006F