Three-Dimensional Local Morphing Waverider Aerodynamic Inverse Design Method and Its Application

Single-design-point waverider aerodynamic layouts cannot adapt to complex flight conditions; therefore, a novel three-dimensional local morphing waverider aerodynamic inverse design method is proposed. This method controls the local wall pressure distribution under a fixed three-dimensional incident curved shock to achieve local morphing, dividing the waverider into shock-determined and pressure-determined regions for dual three-dimensional aerodynamic constraints. Inviscid numerical simulations of a five-shape local morphing waverider show good agreement between the three-dimensional curved shock and Computational Fluid Dynamics (CFD) results (maximum flowfield pressure error approximately 0.91%), verifying that the method is reliable. Adjusting the pressure in the pressure-determined region induces significant variations in the lift-to-drag ratio (68.4%), center pressure ratio (235.7%), and pressure center position (19.1%). Compared with a constant-parameter cone-derived waverider (same leading edge, similar volume), most local morphing shapes have higher viscous lift-to-drag ratios at Ma 6–10, with approximately a 52.1% lift-to-drag ratio variation and an approximately 27.3% pressure center position shift, demonstrating superior aerodynamic performance and wide-speed adaptability.