Investigating the effect of the placement of the split drag rudder control system along the wing span of a flying wing aircraft on rolling and yawing moments.

In this research, the placement of the split drag control system along the length of the UAV wing and its effect on the aerodynamic coefficients are numerically investigated. This control system consists of two plates on top of each other, which, when opened, creates a pressure drag in one wing. This system is used to create a yawing moment in flying wing airplanes. Flying wing airplanes have a high sensitivity for determining the location of control surfaces due to the presence of the swept back angle in the wings and the formation of the wing apex vortex at high angles of attack in this type of configuration. Here, for the installation and positioning of the split drag control system, from a static point of view, it is necessary to install the moving surfaces of the split drag at the end of the wing, because the maximum moment arm will be in this part, which causes the production of the maximum yawing moment; However, from the aerodynamic point of view, the placement of the control surface in this range always has disadvantages due to the existence of the wing tip vortex and the wing apex vortices. Therefore, here it has been trying to place the split drag system in 3 different opening angles in 3 longitudinal positions relative to the tip of the wing and check the resulting moments in different angles of attack. The aim of this research is to increase the yawing moment and decrease the rolling moment coefficients.