Numerical investigation of fuselage-stabilizer-control surface interference for a hypersonic waverider vehicle

In this paper, the interference characteristics and mechanism among the fuselage-stabilizer-control surface which affect the efficiency of the control surface is studied through numerical simulation. The influence of fuselage and stabilizer (including the horizontal distance and vertical distance between the stabilizer and control surface) on the control surface efficiency is exposed and the interference mechanism is revealed. According to the simulation results, some conclusions can be drawn: (1) the existence of the waverider vehicle's fuselage, the existence of stabilizer, and the horizontal and vertical distance between stabilizer and control surface will affect the control surface efficiency; (2) by analyzing the flow interference mechanism, we find that the fuselage's lower Mach number region, the trailing-edge wake, the shock waves and tip vortex wake of the stabilizer, have a negative influence on the control surface. The influence of fuselage's lower Mach number region and the trailing-edge wake are stronger than that of shock waves and tip vortex wake of the stabilizer; (3) through the detailed analysis of the flow patterns, we get the following guidance for the waverider vehicle's layout design: in order to reduce the negative interference on the horizontal control surface efficiency, the horizontal control surface should be mounted in a position away from the stabilizer's trailing-edge wake as far as possible.