二元内并联进气道高速通道优化设计OA

To enhance the wide Mach number performance of the high-speed channel in a two-dimensional internal parallel inlet,a multi-point and multi-objective optimization design method based on fully parameterized flow-path modeling was proposed.An integrated parametric model of the external and internal compression sections was first developed,thereby revealing the nonlinear response and strong coupling mechanism between the performance of the high-speed channel and the design parameters.On this basis,the Kriging surrogate model and the NSGA-Ⅱ algorithm were combined to collaboratively optimize the performance at both the design point(6.0Ma)and the off-design point(4.0Ma).The optimized configuration exhibits significant performance improvements across the wide-speed range.Compared with a conventional three-wedge inlet,the optimized inlet achieves a 6.4％increase in total pressure recovery at the design condition(6.0Ma),and at the off-design condition(4.0Ma),the mass-flow coefficient and total pressure recovery coefficient are enhanced by 9.8％and 4.8％,respectively.The"modeling-analysis-optimization"integrated design framework developed in this study effectively addresses the issues inherent in traditional hypersonic inlet design,such as insufficient coupling between the external and internal compression sections and the difficulty in achieving balanced performance across a wide Mach number range.