Afterbody/nozzle optimal design of hypersonic vehicle

Through combining design of experiment (DOE), surrogate models with genetic algorithms, modified optimization method was built, which was applied in the integrated design of afterbody/nozzle of a hypersonic vehicle. The sequential global surrogate models were developed to satisfy the computational demand. The issue of modifying genetic algorithms included the real number coding, niche technique and multi-objective class&rank skill. In the optimization question, precise computational fluid dynamics(CFD) were used, thrust and lift were used as the performance objects, moment were used as constrain, and the Pareto front was gotten. After the optimization, the thrust and lift force of the nozzle has a great improvement. As a method, this algorithm can be applied in the optimization design with a more complex flow model.