High-Efficiency Optimization Method And Application Research Of Supersonic/Hypersonic Inlet

An optimization system based on adjoint equations was established in this paper.The system was used to study the inverse design of two-dimensional inlet,the optimization of two-dimensional inlet and three-dimensional complex aerodynamic configurations.Firstly,an optimization system was constructed based on adjoint method in this paper.Each part of the system was tested and verified before the optimization study.The five parts were integrated together into a complete system for the optimization with adjoint method.Secondly,the inverse design of the two-dimensional inlet was studied using the system.In this paper,the inverse design problem was transformed into an optimization problem.The difference between the target pressure distribution on the wall and the pressure distribution on the wall of the current configuration was taken as the objective function of the optimization problem.The inverse design method of two-dimensional inlet with preassigned pressure distribution was established,and the parameterization studies of free-stream mach number and pressure gradient were studied.The results show that the pressure distribution of the inlet designed by the method based on adjoint equations is closer to the target pressure distribution than that designed by the method based on the characteristic theory.At the same time,the designed and off-designed points of two-dimensional curved shock compression inlet which can generate elastic deformation were optimized based on adjoint equations.For the designed point of mach number of 3.5,the total pressure recovery of the designed point was optimized from 0.666 to 0.696.The total pressure recovery optimization of eight groups of off-designed points was carried out,and great results were obtained,which provided a guidance for the optimization of off-designed points.Finally,the three-dimensional complex aerodynamic configurations,especially the threedimensional inlet and lift body,was optimized based on the adjoint equations.For the three-dimensional rectangular curved shock compression inlet,the total pressure recovery was increased from 0.836 to 0.922,10.3% relatively.For the REST inlet,the total pressure recovery of throat was increased from 0.748 to 0.811,which increased by 8.4% relatively.For the lift body with a designed mach number of 5.0,the lift-to-drag ratio was increased from 3.30 to 6.65,101.5% relatively,which achieving obvious effect.