基 于 离 散 伴 随 的 高 超 内 转 式 进 气 道 气 动 优 化 设 计

Despite its relatively good inlet capture ability and high air compression efficiency，the inward turning inlet cannot be locally adjusted in the preliminary design，and improvement in the adverse effects of complex flow structures such as flow separation and secondary flow caused by shock/boundary layer interference is difficult. Therefore，perfor⁃ mance optimization is necessary. The current design optimization of the hypersonic inward turning inlet faces many challenges such as the complex profile，large-scale design variables，and the high accuracy requirement of the flow⁃ field numerical simulation. The gradient optimization method based on discrete adjoint is adopted to carry out the aero⁃ dynamic design optimization for the inward turning inlet with a wedge forebody. The optimization results show that the undulating shape of the inner and outer compression sections significantly changes the internal shock structure，re⁃ duces the wall pressure gradient，and thereby abates the streamwise vortex. In addition，the interference intensity be⁃ tween the shock train and the boundary layer in the isolation section is significantly weakened，inhibiting the expansion of the low energy flow region. Under the design condition，compared with the initial configuration，the aerodynamic performance of the optimized configuration is significantly improved. The total pressure recovery coefficient，the flow coefficient and the pressure ratio at the exit are increased by 8. 767%，0. 163%，and 0. 763%，respectively，while the drag is reduced by 1. 658%.