This research aims to study temperature and Reynolds number scaling effects in double-fin generated crossing shock-wave/turbulent boundary-layer interactions (SWTBLI). This geometry is selected as it represents a simplified supersonic inlet. Vehicles intended for supersonic flight go through a vast range of altitudes and velocities throughout its flight, thus drastically changing temperatures and Reynolds numbers experienced by the inlet. Understanding how this interaction behaves throughout its flight domain is beneficial to design work.
One design goal of a successful inlet is to provide as uniform air as possible into the combustor. Large separation caused by the SWTBLI causes significant pressure distortion within the flow field. This reduces the overall efficiency and performance of the engine as a whole.
This work aims to determine how this distortion scales with temperature and Reynolds number. It also hopes to investigate how such distortion may be reduced through the use of passive flow control. Vortex generators with heights less than the boundary layer thickness will be placed upstream of the interaction, and their effects on the total pressure and pressure distortion will be studied.
General schematic of the flow field surfaces with flow in the positive x-direction.
Mach number contours on a double-fin-generated crossing SWTBLI. Flow is from left to right looking top-down.
Surface pressure contours and u = 0 m/s iso-surfaces with velocity ribbons. Flow is in the positive x-direction.
Total pressure contours at outlet.