Forced Shock Oscillation Control in Supersonic Intake Using Fluid-Structure Interaction

This paper proposes a fluid-structure interaction-based method to restrict the undesirable shock oscillation process due to the downstream pressure perturbation and limit its adverse impact on a two-dimensional supersonic intake. A computational framework is established to illustrate the coupled solutions between the forced shock oscillation and the nonlinear structural vibration. Complex intake aerodynamics are captured with an implicit finite volume method. Finite element code is employed to determine the dynamic response of a flat flexible wall locally installed in a rigid cowl wall. Data transfer between the two physical fields is accomplished with a partitioned coupling scheme. The large-amplitude shock oscillation and poor variation in aerodynamic performance are found in the uncontrolled transient flow solutions of the rigid wall intake model. Conversely, a shock oscillation amplitude reduction of about 50% is achieved by the local flexible wall, and it shows an improvement to the aerodynamic performance of the supersonic intake as well. This paper demonstrates that the dynamic cavity generated by fluid-structure interaction contributes to outstanding performance of this new method. Additionally, the impact of the dynamic cavity is interpreted by two fundamental mechanisms: the local enlarged flowpath with a convergent-divergent shape and energy transfer within the fluid-structure interaction.