超声速巡航导弹轴对称进气道型面优化设计

针对超声速轴对称式进气道进行型面优化设计.以最大总压恢复系数为目标函数,进行锥体斜激波系的优化设计,迭代计算出超声速段锥体斜激波系的最佳优化配置;按照一维绝热、无粘假设进行超声速混压式进气道的起动设计;在亚声速扩压器优化设计中采用多模块等面积扩压规律,有效地避免喉道后扩张-收缩结构的出现,改善高马赫数下的气流分离特性....

Optimization Design of Axisymmetric Inlet of Supersonic Cruising Missile

This paper gives optimization design of an axisymmetric supersonic inlet.To achieve the maximum total pressure recovery coefficient,the optimal allocation of a series of supersonic oblique shock waves,passing by a cone configuration,has been calculated using an iterative program.In accordance with the one-dimensional adiabatic,inviscid theory,the start design method of supersonic mixed-compression inlets has been presented.Finally,optimal design of the subsonic diffuser is given with the multi-module equal ...