A new method is developed for modeling helicopter high-speed impulsive (HSI) noise. The aerodynamics and acoustics near the rotor blade tip are computed by solving the Euler equations on an unstructured grid, A stationary Kirchhoff surface integral is then used to propagate these acoustic signals to the far field, The near-field Euler solver uses a solution-adaptive grid scheme to improve the resolution of the acoustic signal, Grid points are locally added and/or deleted from the mesh at each adaptive step, An important part of this procedure is the choice of an appropriate error indicator, The error indicator is computed from the flowfield solution and determines the regions for mesh coarsening and refinement, Computed results for HSI noise compare favorably with experimental data for three different hovering rotor cases.
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