Numerical study on influence of fuselage and stabilizer on control surface efficiency and interference characteristics for a hypersonic waverider-derived configuration

In this paper, the hypersonic flow around waverider-derived vehicle has been numerically simulated by solving Reynolds-averaged Navier-Stokes equations. The influence of the key parameters on the control surface efficiency is obtained and the interference mechanism is explored. According to the simulation results and their analysis, some preliminary conclusions can be drawn: (1) the horizontal and vertical distance between stabilizer and control surface, and the existence of the waverider-derived vehicle's body will affect the control surface efficiency; (2) whether with or without fuselage, the same affecting trend are obtained by the horizontal and vertical distance between stabilizer and control surface; (3) under the angle of attack of 4°, the horizontal distance has little disturbance on control surface efficiency; in order to increase the longitudinal static stability of the vehicle, the stabilizer can be mounted reasonably close to the control surface; the vertical distance has large influence on the control surface efficiency; therefore, to reduce the amount of interference on the horizontal control surface effectiveness, the stabilizer should be mounted in vertical position as high up as possible; (4) with the presence of the body, the root part of control surface is strongly interfered with by the body's lower Mach number region, hence nearly 20% efficiency is lost compared with the condition without the body. Preliminary conclusion, we believe, are of some quantitative and qualitative value to waverider-derived hypersonic vehicle design.