Simulation of Unsteady Flow Actuation Produced by Surface Plasma Actuator on 2 - D Airfoil
Effect of flow actuation driven by low current DC surface glow discharge plasma actuator is studied numerically by using OPENFOAM.Numerical model of the source of flow actuation is obtained by physical modeling of ion pressure rise created in DC plasma sheath near the cathode.Modeled plasma flow actuator is tested with NACA0012 airfoil in order to demonstrate the actuation effect in low speed flows.Dynamic situation of the airfoil is obtained by rotating the airfoil within a certain range of angle of attack at a specific rotating speed.In order to simulate the motion of oscillating airfoil,computational domain is split into two parts; far field and near the airfoil.Sliding mesh is applied to a circular domain near the airfoil.To simulate unsteady plasma actuator,plasma actuator is added in Navier Stockes equation in term of body force.Simulated plasma actuator is placed on the upper surface of the airfoil at different positions.As the angle of attack changes,flow around the airfoil produces various drag and lift force and dynamic stall may happen.By changing actuation authority according to the change in angle of attach,stabilization of unsteady flow field is achieved and hence constant aerodynamic performance is maintained.The relevant relationship between frequency of plasma actuator and reduced frequency is investigated.
Plasma Actuator Flow Control Oscillating Airfoi Dynamic Mesh OpenFOAM
Phan Minh Khang Jichul Shin
E-vehicle Institute,University of Ulsan,Ulsan,680-749,Korea Department of Aerospace Engineering,University of Ulsan,Ulsan,680-749,Korea
国际会议
2014 Asia-Pacific International Symposium on Aerospace Technology(2014亚太航空航天技术学术会议)
上海
英文
1-14
2014-09-24（万方平台首次上网日期，不代表论文的发表时间）