Reducing the rolling moment coefficient in the use of split drag rudder system using wing fences

In this research, wing fences have been designed using the parametric study method. Here, by deflecting the vortices of the wing apex, the excess rolling coefficient produced by the split drag rudder system has been reduced. This control system is used to generate yawing moment in flying wing UAVs. The size of the fences is selected based on the dimensions of the vortex at different AOA. In this research, the survival equations are discretized by the finite volume method, then the discretized algebraic equations are solved by the Simple C algorithm. In this simulation, the K-W-SST two-equation model is used to model the turbulent flow. The UAV used in this experiment is a lambda-shaped flying aircraft. The produced fence was installed at three different heights and three different positions along the wing, which were investigated at high AOA. The results show that the use of fences in all AOA will not be suitable from an aerodynamic point of view; But finally, the most optimal location of the fence will be introduced to reduce the disturbing rolling moment coefficient.