Computational Considerations for the Simulation of Shock-Induced Sound

The numerical study of aeroacoustic problems places stringent demands on the choice of a computational algorithm,because it requires the ability to propagate disturbances of small amplitude and short wavelength. The demands are particularly high when shock waves are involved, because the chosen algorithm must also resolve discontinuities in the solution. The extent to which a high-order-accurate shock-capturing method can be relied upon for aeroacoustics applications that involve the interaction of shocks with other waves has not been previously quantified. Such a study is initiated in this work. A fourth-order-accurate essentially nonoscillatory (ENO) method is used to investigate the solutions of inviscid, compressible flows with shocks in a quasi-one-dimensional nozzle flow. The design order of accuracy is achieved in the smooth regions of a steady-state test case. However, in an unsteady test case, only first-order results are obtained downstream of a sound-shock interaction. The difficulty in obtaining a globally high-order-accurate solution in such a case with a shock-capturing method is demonstrated through the study of a simplified, linear model problem. Some of the difficult issues and ramifications for aeroacoustic simulations of flows with shocks that are raised by these results are discussed. Research Assistant Professor, Department of Aerospace Engineering, Old Dominion University, Norfolk, VA 23529; supported by U.S. Government grant NAG1-1653. yResearch Engineer, Fluid Mechanics and Acoustics Division, NASA Langley Research Center, Hampton, VA 23681. 1