Experimental study of the effect of AMT on aerodynamic performance of tailless flying wing aircraft

The inherent aerodynamic characteristics and control effectiveness of AMT (All-Moving Tip) of a tailless flying-wing configuration aircraft were investigated in wind tunnel. The results showed that the tested configuration is static stable in longitudinal axis, however, the zero lift pitching moment coefficient is around zero, which is adverse to takeoff and landing. When AMT deflects, the drag coefficient of the aircraft increases, and the nose-up moment increases too, but the maximum lift to drag ratio decreases. The deflection of single AMT could provide considerable yaw control moment almost without variation of lift coefficient, and cause relative large rolling and pitching moments. Furthermore, it is obtained that the coupling between deflection of single AMT and side force is weak. The effects of both AMTs simultaneous deflection and single AMT deflection on longitudinal aerodynamic characteristics are similar, but the impact of AMTs simultaneous deflection is stronger.