A Conceptual Study of Wing–Rudder Integrated Aerodynamic Configuration for Wide-Speed-Range Vehicles

To reconcile high- and low-speed aerodynamic adaptation with tailless stability and control, a wing–rudder integrated tailless configuration is proposed. Morphing wing–rudders mounted at the wingtips of a cranked double-swept waverider deflect about the body longitudinal axis rather than the conventional spanwise hinge axis, combining morphing and control-surface functions in one component while eliminating the V-tail. Aerodynamic characteristics are obtained by numerical simulation across transonic, supersonic, and hypersonic regimes, with the solver validated against the AGARD-B standard model. The influence of symmetric deflection on the maximum lift-to-drag ratio diminishes with increasing Mach number: the optimal deflection improves it by less than 2% relative to the neutral position, and a 6.6% enhancement over the V-tail baseline is achieved at the transonic condition. Downward deflection functions as an adjustable ventral fin that restores directional static stability across the speed range, the rudder supplying a major share of the restoring yawing-moment derivative at full deflection. At the same deflection, however, differential yaw control effectiveness collapses, creating a conflict between the demands for directional stability and yaw control, the core characteristic of this configuration. The integrated layout achieves wide-speed-range lift-to-drag efficiency, tailless lateral–directional stability and control, and low radar cross-section with a simple structure.