Separation Control Inside a Rectangular Supersonic Inlet Using Dielectric Barrier Discharge Plasma Actuators

Abstract

A parametric 2D computational fluid dynamics (CFD) study of flow control within a supersonic air inlet using surface dielectric barrier discharge (SDBD) plasma actuators was performed. The objective of this study was to establish receptive locations and orientations for the SDBD actuators where the actuator effects would be most pronounced and to assess the potential for SDBD actuators to increase the total pressure recovery and decrease the total pressure distortion of a rectangular supersonic inlet in Mach 2.5 flight. Linear plasma actuators were modelled as a time-averaged body force. Ultimately, 2D results demonstrated limited influence on the supersonic flow within the inlet across all locations, orientations, and actuator strengths tested for linear actuators which apply their force primarily in the streamwise direction. Based on the results, 3D CFD simulations of different actuator geometries are planned for the future direction of the current research.