格子ボルツマン法による翼後縁騒音の予測と制御に関する数値的研究

抄録

The tone noise is known as an aerodynamic noise generated from a two-dimensional airfoil placed in a flow, which is said to be attributed to vortices shedded from the trailing edge of the airfoil. Commonly, the trailing edge shape of an airfoil is uniform in the span direction from the viewpoint of manifacturing and structural strength, but the vortex shedding becomes coherent in the spanwise direction, resulting in the increase in the tone noise. In this study, simultaneous calculations of the flow field and sound field were performed using the lattice Boltzmann method for the tone noise generated from the NACA0012 airfoil. We investigated the influence of the spanwise trailing edge shape on the vortex shedding causing the tone noise.