In this paper the aeroacoustics of leading-edge slat devices in a high-lift configuration are investigated computationally. In order to perform parametric studies of the aeroacoustics, a simplified two-dimensional model of the slat is used. The acoustics are computed using a linearized Euler solver, with an acoustic source located at the slat trailing edge, the location and strength of which is determined both experimentally and through unsteady RANS simulations. The linearized Euler solver

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... 6 th -order pre-factored compact differencing for spatial derivatives and a 4 th -order low-dissipation, low-dispersion Runge-Kutta scheme for time integration. A buffer zone boundary condition is used to prevent the reflection of outgoing acoustic waves from contaminating the solution. The code uses a multi-block strategy on curvilinear meshes and is run on PC workstations. The LEE computations are compared with a hybrid unsteady RANS and Ffowcs-Williams Hawkings approach to evaluate the applicability of the LEE method for this class of problem.