Waverider design based on osculating theory presents two critical issues: robust specification of design curves and accurate solution of the basic flowfield. Although the existing parametric approaches have advanced rapid configuration generation through geometric parameterization frameworks, they critically neglect the inherent coupling between aerodynamic constraints and geometric design parameters. To overcome this limitation, an Aerodynamics-Informed Parametric (AIP) method is developed by analytically deriving three waverider design curves and integrating them with the second-order curved shock theory. This method enables rapid waverider surface design while accounting for inflow conditions and shock wave geometry. Three typical waveriders, each featuring distinct combinations of design curves as inputs, are constructed and evaluated through inviscid and viscous numerical simulations to validate the applicability and accuracy of the AIP method. The results indicate that waveriders derived using the AIP method successfully reproduce the preassigned shock waves and original flowfields. Compared to traditional waverider design techniques based on the method of characteristics, the AIP method reduces computation time by approximately 94 %, while maintaining errors in the inviscid lift-to-drag ratio, viscous lift-to-drag ratio, and volumetric efficiency below 0.1 %, 4.0 %, and 0.1 %, respectively. Additionally, a specially designed model is fabricated for the wind-tunnel tests to analyze the hypersonic aerodynamic performance of the waverider. Both numerical and experimental results confirm the feasibility of the AIP method, making it a promising candidate for waverider design and optimization.

Using the most phenomenon of common shock wave in hypersonic flow for aerodynamic profile design is one of the important directions of aircraft research. To solve the three-dimensional curved shock flow field more accuratelyand efficiently, a new inverse design method, called the method of three-dimensional curved stream-surface, is proposed for the design of waverider. The new method discretizes the pre-given three-dimensional curved shock surface into multiple flow surfaces, and calculates the flow field in the curved flow surface according to the aerodynamic parameters of the stream-surfaceand their derivatives. In this way, the streamline in the calculation process is always in the curved stream-surface. Two shock waves with different three-dimensional characteristics are specified as input to prove the effectiveness of this method. The results show that the wall pressure ratio error is less than 1.07% in the conical flow fieldand the elliptic curved cone flow field compared with inviscid CFD results. At the same time, this method is applied to the design of waveriders for specified elliptic conical shock. The accuracy of this method for the design of waverider is verified by inviscid CFD simulation, with the maximum wall pressure ratio error being only 0.26%and the calculation timeand resources being reduced by about 40% compared with the Local-Turning Osculating Cones Method under the same conditions. Therefore, the method of three-dimensional curved stream-surface can greatly improve the scopeand efficiency of the waverider design, and is conducive to the design of the aerodynamic system of hypersonic vehicle.