宽速域高超声速飞行器是航空航天领域新的战略制高点，其飞行速域与空域极大化特点导致亚/跨/超/高超声速气动性能难以兼顾。为了缓解高低速气动设计的矛盾，以典型宽速域乘波-机翼布局为研究对象，结合基于代理模型的全局优化方法和基于伴随梯度的局部优化方法，对该宽速域构型的布局参数和剖面形状进行了从全局到局部的多目标分步优化。结果表明，在约束亚声速升力系数、高超声速阻力系数的情况下，基于代理模型的布局参数优化方法能够在维持高超声速气动性能的同时，将亚声速的升阻比提升9.5%。进一步选取布局参数优化结果Pareto面上亚声速气动特性最优的构型，利用基于伴随梯度的优化方法，对机翼剖面进行梯度优化。优化结果表明，梯度优化能够有效地改善飞行器亚/高超声速状态下的阻力特性，并将翼型在几何上优化为兼顾亚/高超声速气动特性的双S翼型。通过上述从布局参数到剖面参数的优化，乘波-机翼构型的亚声速升阻比相比初始构型提升了12.4%，高超声速升阻比相比原始构型提升了6.2%。

Wide-speed-range hypersonic vehicle， as a new strategic high ground in the aerospace field， face the challenge of balancing subsonic aerodynamic performance with transonic and supersonic as well as hypersonic characteristics due to the maximization of their flight speed and altitude range. To alleviate the high and low speed aerodynamic design conflict， this paper combines a global optimization approach based on surrogate models with a local optimization approach based on adjoint gradients to perform a multi-objective stepwise optimization of the layout parameters and airfoil shapes of the wide-speed-range configuration， spanning from the global to the local scale. The results indicate that under the constraints on subsonic lift coefficient and hypersonic drag coefficient， the layout parameter optimization method based on surrogate models can enhance the subsonic lift-to-drag ratio by 9.5%， while maintaining hypersonic aerodynamic performance. Furthermore， by selecting the configuration on the Pareto front of layout parameter optimization results with the optimal subsonic aerodynamic characteristics， a gradient optimization of the wing profile is performed using an adjoint gradient-based method. The optimization results demonstrate that the gradient optimization effectively enhances the drag characteristics during subsonic and hypersonic cruising states， leading to the geometric optimization of the airfoil as a dual-S shape that balances subsonic and hypersonic aerodynamic characteristics. Through the aforementioned optimization from layout parameters to profile parameters， the subsonic lift-to-drag ratio of the waverider-wing configuration increased by 12.4% compared to the original configuration， while the hypersonic lift-to-drag ratio improved by 6.2% compared to the original configuration.