Mathematical Fluid Dynamics of Plasma Flow Control over High Speed Wings

摘要

This report summarizes modeling of surface dielectric barrier discharge (SDBD) and flow control. A physics-based phenomenological model was used for analytical approximations of SDBD-induced body force and heat source, which were incorporated into a Navier-Stokes solver for CFD studies. Results show that a SDBD actuator can strongly affect laminar boundary layers and that tangential jets or concentrated vortices can be generated in the near-wall flow, thus making SDBD actuators attractive for control of boundary-layer separation and laminar-turbulent transition. CFD studies of vortex flow past a delta wing at high angles of attack were carried out to estimate feasibility of flow control using SDBD actuators. Results show that for a delta wing with sharp leading edges of 60 deg. sweep angle at free-stream Mach number 1.5, the flow control strategy should focus on vortex breakdown. For actuators at the wing- apex, leading-edge, and multi-element SDBD actuators, the vortex-breakdown locus can be controlled, although the integral aerodynamic forces are weakly affected and SDBD forcing can cause unsteady oscillations of the vortex breakdown.