抄録
The supersonic flow past a cavity induces large pressure oscillations that may create many undesirable effects in aerospace applications. Those pressure oscillations may lead to the occurrence of resonance in the cavity. This resonant cavity causes to increase aircraft noise and drag. For these reasons, the area of cavity flow has attracted the researchers for years. In spite of numerous research investigations, the understanding of the flow physics governing the behavior and the practical methods of suppressing cavity-induced pressure oscillations have not yet been studied adequately. In the present study, a new passive control technique has been investigated numerically by modifying the front wall of a square cavity with flat and spherical surfaces. The objective of the study is to determine the effectiveness of the proposed control devices as oscillation suppressors.
