Computational Fluid Dynamics and Proper Orthogonal Decomposition Based Control of Flow Over Supersonic Cavities

Abstract

A Computational Fluid Dynamics (CFD) study is conducted to investigate the unsteady, turbulent supersonic cavity flow characteristics and to control the severe effects of the flow field. Simulations of Mach 1.5 supersonic cavity flow with a length to depth ratio of 5.07 are performed using commercial ANSYS Fluent solver. Unsteady density-based Reynolds Averaged Navier-Stokes equations are modeled with standard k-? turbulence model. Both baseline simulations with no control and simulations with passive and active control methods are examined. Implemented passive control methods are trailing edge wall inclination, cavity entrance cover plate, and wall spoilers. Microjet blowing is applied as an active control method. For further investigation of the flow field and to distinguish the dominant features of the controlled and uncontrolled cases, Proper Orthogonal Decomposition (POD) is applied to velocity data obtained from the inside of the cavity. CFD and POD studies represent promising results for flow control in terms of suppressing undesired effects of cavity flow oscillations. © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.