Abstract
An unsteady two-dimensional inviscid blade-vortex interaction has been calculated using the finite difference lattice Boltzmann method of the compressible Euler model. The perturbed discrete Boltzmann equation based on a prescribed vortex approach has been proposed to prevent a vortex from diffusing by numerical dissipation. The discretization of the governing equation is based on a second-order-accurate explicit Runge-Kutta time integration and a fifth-order-accurate upwind scheme that includes additional terms to capture the shock waves clearly. Subsonic and transonic flows around an airfoil were simulated to validate the perturbed discrete Boltzmann equation system. The numerical results were compared with other numerical data, and good agreement has been obtained. In the simulation of the transonic blade-vortex interaction, an instantaneous pressure coefficient, a time history of a lift coefficient, and patterns of acoustic waves were compared with other numerical results, and were found to agree with them very well. We have also investigated a generation mechanism of acoustic wave caused by the blade-vortex interaction, the effect of the flow Mach number, and the influence of the vortex miss distance.
Published Version
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