Shock Oscillations in Diffuser Modeled by a Selective Noise Amplification
Shock waves in supersonic flow oscillate under certain conditions. These oscillations usually have negative effects, especially for flow past transonic airfoils and in supersonic diffusers. It is therefore of practical importance to understand the origin and the consequences of these oscillations. We model and predict some physical characteristics of self-sustained shock oscillations in transonic diffuser flows. We first give the results of a quasi-one-dimensional stability analysis. The mean flow is calculated with a code solving the averaged Navier-Stokes equations. The present stability approach however is limited to the core region where the viscous effects can be neglected