Using high-order accurate essentially nonoscillatory schemes for aeroacoustic applications

The numerical study of aeroacoustic problems places stringent demands on the choice of a computational algorithm, particularly when shock waves are involved, Because of their dual capacity for high-order accuracy and high-resolution shock capturing, the recently developed class of essentially nonoscillatory (ENO) schemes has generated considerable interest in regard to such problems. The use of ENO schemes for aeroacoustic applications is investigated, with particular attention to the control of the adaptive stenciling procedure. A modification of previously developed stencil-biasing procedures is proposed. This nonlinear stencil biasing allows a freer adaptation near discontinuities than is allowed by the previous biasing methods, without disturbing the biased, stable stencils that are desired in smooth regions. The accuracy of these new methods is validated through the study of a shocked nozzle flow. An axisymmetric shock-vortex interaction is then investigated, Numerical results indicate a reduction in error when compared with results in which other stencil-biasing procedures are used.