基 于 离 散 伴 随 的 高 超 声 速 密 切 锥 乘 波 体气 动 优 化 设 计

The design method of osculating-cone waverider based on planform-controllable shape can significantly im⁃ prove the design flexibility and overall lift-drag characteristics for traditional waveriders. However，because the three-dimensional effect，the viscous effect and the passivation effect of the head/leading edge are ignored in the design of the waverider，overflow still occurs under the design conditions leading to the difficulty in achieving the optimal lift-to-drag ratio. In addition，the lift-drag characteristics will still be poor when the waverider is not in design conditions. In this paper，an aerodynamic shape optimization design method for the hypersonic vehicle based on discretized adjoint is constructed by combining the CFD solvers based on the full-velocity flux solution method and the RANS turbulence model，the robust automatic structured mesh wrapping method，the free form deformation geometry parameterization method，the discretized adjoint method and the sequential quadratic programming algorithm. Through this method，the single point and multi-point three-dimensional aerodynamic optimization designs of the whole aircraft are carried out for the planform-controllable osculating-cone waverider. Under more than 4 million structural grids，600 design vari⁃ ables and 303 design constraints，the proposed method only takes 2 240 CPU hours and 3 360 CPU hours to achieve the single point and multi-point optimization designs of the waverider. The results show that compared with the initial configuration，the lift-drag ratio of the single point optimization configuration in the design state increased by nearly 5%. The configuration obtained by multipoint optimization can ensure that the lift-drag ratio at off-design states is in⁃ creased by more than 10% without loss of lift-drag characteristics at design state，which improves the theoretical limita⁃ tions of the planform-controllable osculating-cone waverider to a certain extent.