Influences of panel vibration on supersonic compression corner flow characteristics

As a typical flow structure in hypersonic vehicles, the shock wave/boundary layer interaction in compression corners leads to increasingly prominent structural vibration issues due to aerodynamic heating and lightweight design requirements. In this study, the influences of panel vibration with different amplitudes and frequencies on the supersonic compression corner flow characteristics are numerically studied. The results show that in all calculation cases, as the panel amplitude increases, the size of separation bubble at the corner gradually decreases during moments when no separation bubble is generated in the panel region. When the panel amplitude increases to a certain value, a separation bubble is generated in the panel region during the period of large panel concavity. This causes the size of the separation bubble at the corner to significantly increase and the separation shock to significantly move upstream and then leads the high-frequency proportion in the pressure fluctuation in the panel region to increase and the skin friction coefficient to decrease significantly. As the panel vibration frequency increases, the generation of the separation bubble in the panel region is gradually delayed. When the panel vibration frequency increases to a certain value, the separation bubble will not be generated in the panel region. As the panel vibration frequency further increases, the separation bubble at the corner almost disappears during the period of small panel concavity. This study can enhance the understanding of the influences of panel vibration on the compression corner flow characteristics.