Numerical Study on Control of Normal Shock-Boundary Layer Interaction in Supersonic Inlet

摘要

A numerical model for the integration of inlet and boundary layer bleed system was developed, and the impact of boundary layer bleed in normal shock wave zone on inlet flow field and its performance was studied by solving the flow field governing equations using the finite volume method. Results indicated that the boundary layer bleed system can significantly increase the back pressure of inlet in its critical operation status, reduce the separated back flow region caused by shock wave -boundary layer interaction, and enhance the total back pressure of shock wave. Therefore, the boundary layer bleed system is an efficient method for the control of normal shock wave -boundary layer interaction.