プラズマアクチュエータによるキャビティ音制御に関する直接計算

抄録

To clarify the mechanism of the control of cavity tone by plasma actuators of which electrodes are aligned with the oncoming flow, direct aeroacoustic simulations were performed along with wind tunnel experiments. The effects of the pitch of the actuators are focused on. The measured results show the most intense reduction of cavity tone is attained at the ratio of pitch to boundary layer thickness, p/δ = 10.9. The predicted results elucidate longitudinal vortices in the controlled cavity flow, which are originally generated by the actuators. By these longitudinal vortices, the large-scale vortices with the spanwise axis related with cavity tone are weakened and have spanwisely non-uniform structures.