为提升高超声速飞行器的升阻比，一种重要设计思想是让飞行器各组件的激波、膨胀波产生有利的相互作用，获得增升、减阻的效果。基于上述设计思想的高升阻比构型通常根据无黏二维/轴对称流场的激波-膨胀波关系设计。由于三维效应与空气黏性的影响，其实际性能相比理想设计性能往往存在较明显的退化。针对上述问题，提出流场波系引导的优化设计方法。不同于以气动性能指标为目标的传统优化方法，该方法以设计流场的波系形态为目标引导几何参数的优化方向。设计方法在一种主翼、上翼产生有利干扰的三维消波翼的设计中得到应用验证。通过将优化构型的流场、气动性能与根据二维无黏方法设计的初始构型对比，证明了优化设计方法的有效性。通过与菱形翼对比，验证了消波翼在设计工况下相比于常规构型的升阻比优势。

To improve the lift-to-drag ratio of hypersonic vehicles， an important idea is to construct favorable interactions between shock waves and expansion waves forming on different parts of the vehicle. In the existing design methods based on this idea， the geometric parameters are calculated by the shock-wave and expansion-wave relationships of two-dimensional or axisymmetric inviscid flow fields. Due to the influence of three-dimensional effect and viscosity， the high lift-to-drag ratio configurations designed by existing methods shows significant performance degradation compared with ideal design performance. To solve this problem， an optimization design method derived by shock-wave morphology is proposed. This method takes the target shock-wave morphology instead of the aerodynamic performance as the objective to guide the optimization direction of geometric parameters. The method is applied to a three-dimensional wave cancellation biplane where the main wing and the upper wing have favorable interference. The optimized configuration outperforms the initial configuration designed by the two-dimensional inviscid method in terms of both shock-wave morphology and aerodynamic performance， which proves the effectiveness of the proposed optimization design method. Compared with the diamond wing， the wave cancellation biplane has the advantage in the lift-to-drag ratio under the design condition.