Abstract

This study focuses on tail aerodynamic modeling with CFD simulation of an experimental unmanned aerial vehicle (UAV) in horizontal and vertical section separately. This aircraft with special capabilities has moderate maneuver performance, and predicting the aerodynamic behavior requires knowing that when dynamic stall will occur even in tail. The unsteady nature of the flow field around UAV tail, and the configuration of the generated lift and drag forces must be understood in order to optimize the comfort control system. As a result, flow around the tail and trailing-edge separation of elevator and rudder in horizontal and vertical tail at low Reynolds number with special angle of attack has been simulated .Finally, a custom three- component force balance for measuring lift , drag and moment is described in detail. The results indicate that maximum allowable angles of deflection are about 13 and 17 degree in horizontal and vertical tail, respectively. Moreover, each 1 degree of deflection decreases almost 0.35 degree horizontal tail stall angle.