Paper Title
Numerical Simulation of Helicopter Blade Vortex Interactions Based on the LBM-LES Method

Abstract
In this current research paper, Numerical simulation is performed to predict the vortex airfoil interaction. Combining the LBM (Lattice Boltzmann Method)-LES (Large Eddy Simulation) method, 2D simulations are performed for Reynolds Number 1.3e6 and Mach number 0.5 on NACA 0012 airfoil. The Scully vortex with a core radius r = 0.018, circulation Γ = 0.283 and miss-distance h= 0 has been used to the fully-developed turbulent flow field as a perturbation. To simulate the turbulence, two-dimensional particle velocity model of the LBM method D2Q9, and the Dynamic Smagorinsky subgrid model of LES is used. In this present work, the NACA 0012 is steady and vortex passes through the airfoil. The computation is carried out for three different angles of attack α = 0o, α = 2o and α = 5o. In all cases, the releasing location of the vortex is 0.2m from the airfoil. The result shows that the angle of attack α= 20 is the best angle for reducing the vortex effect on the airfoil among three angles. Index Terms - Computational fluid dynamics, vortex airfoil interaction, AOA- angle of attack, Aerodynamics.