Aero-Acoustic Moldeling using Large Eddy Simulation

The flow-acoustic splitting technique for aero-acoustic computations is extended to simulate the propagation of acoustic waves generated by three-dimensional turbulent flows. In the flow part, a sub-grid-scale turbulence model (the mixed model) is employed for Large-Eddy Simulations. The obtained instantaneous flow solution is employed as input for the acoustic part.

At low Mach numbers the differences in scales and propagation speed between the flow and the acoustic field are quite large, hence different meshes and time-steps can be utilized for the two parts. The model is applied to compute flows past a NACA 0015 airfoil at a Mach number of 0.2 and a Reynolds number of for different angles of attack.

The flow solutions are validated by comparing lift and drag characteristics to the experiments of Shedhal and Klimas. The comparisons show good agreement between computed and measured airfoil characteristics for angles of attack up to stall. For the acoustic solutions, predicted noise spectra are validated quantitatively against the experimental data of Brook et al.

A parametrical study of the noise pattern for flows at angles of attack between 4 deg and 12 deg shows that the noise level is small for angles of attack below 8 deg, increases sharply from 8 deg to 10 deg and reaches a maximal at 12 deg.