Numerical Study of Vortex Flow Control on High-Angle-of-Attack Slender Body

Abstract

We have numerically analyzed the asymmetric separation flow control over a slender body aiming to improve the controllability of high-angle-of-attack flight; in this study, the dielectric barrier discharge (DBD) plasma actuator is used as flow control device. A Reynolds averaged Navier Stokes/large-Eddy Simulation hybrid method (RANS/LES) is adopted with a high-order compact spatial difference scheme. First, the characteristics of flow field were investigated for various angles of attack. The asymmetricity of the flow field becomes stronger with higher angle of attack. In addition, the flow separation point is changed depending on the angle of attack, axial position and body side (starboard or port side). Next, numerical simulations of the flow field controlled by the plasma actuator were conducted. Plasma actuators are located circumferential position of ±80 degrees, ±100 degrees or ±120 degrees. We investigated the influence of the positional relation between the flow separation point and the actuator location on the side force control. As a result, it is shown that the circumferential position of the plasma actuator is important and should be chosen from the position and distance from the flow separation point. In addition, it is considered that the plasma actuator at closer position to the body apex has a stronger impact on the flow field.