翼上大涵道比发动机BWB布局一体化气动优化

Integrated aerodynamic optimization of BWB configuration with high bypass ratio engine

考虑动力影响的气动布局一体化设计是挖掘飞行器设计潜力的重要环节。基于非结构混合网格并行RANS求解器,面向消除梯度计算量对设计变量个数以及变形网格技术的依赖性需求,进行了全过程离散伴随方程的推导。在构造离散伴随方程的基础上,通过迭代反压调整建立精确流量控制进排气数值模拟技术,并推导离散伴随方程边界条件矩阵。进一步以某翼上安装大涵道比发动机翼身融合(BWB)布局为研究对象进行了一体化设计研究。优化结果表明,所提出的优化方法显著提升了气动性能,验证了方法在强约束、考虑动力影响的一体化设计问题中的实用性,为未来翼上布局民用飞机设计提供有力的技术支撑。

The integrated design of aerodynamic configuration considering the dynamic influence is an important method step to tap the potential of aircraft design.The whole process discrete adjoint equation with the aim of eliminating the dependence of gradient calculation on the number of design variables and deformation grid technology is deduced based on the unstructured hybrid grid parallel RANS solver.The accurate flow control numerical simulation technology considering inlet and exhaust is established through iterative back pressure adjustment,and the boundary condition matrix of discrete adjoint equation is derived based on the construction of discrete adjoint equation.Furthermore,the integrated design is studied by taking a BWB configuration as a research object.The optimization results show that the optimization method significantly improves the aerodynamic performance,verifies the practicability of the method developed in this paper in the integrated design problem with strong constraints and considering dynamic effects,and provides strong technical support for the civil aircraft design of BWB configuration in the future.