Numerical analysis of the effect of vortex control mechanism on longitudinal aerodynamics of lifting body

A numerical analysis was carried out on the aerodynamics of a lifting body consisting of a blunted, half-cone geometry. In the present paper, the application of a novel vortex control mechanism in the form of leading-edge rotating cylinders, to alter lift, drag and pitching properties, were performed. For the first time, the use of rotating cylinders to manipulate the swirling vortices above the lifting body for pitch control is reported. This study focuses on flight conditions pertaining to the landing phase. The unsteady Reynolds-Averaged Navier–Stokes (URANS) method for flow simulation is verified and compared with wind-tunnel test. Simulation of lifting body performance is carried out at varying angles of attack with different directions of cylinder rotation and rotation speeds. Leading-edge vortices similar to those formed on delta-wings are observed. Rotating cylinders are shown to be an effective method of controlling the leading-edge vortices. Momentum injection by rotating the cylinders in the direction of the flow can suppress formation of vortices, reducing the lift force, drag force and pitching moment of the lifting body. Rotating in the opposite direction strengthens the vortices, increasing the lift force, drag force and pitching moment. Rotating cylinders are found to offer limited pitch control; regardless, the lifting body studied remains inherently unstable in pitch mode.