二元高超声速进气道内压缩通道/隔离段曲面构型  

Curved surface structure of internal contraction tunnel/isolator of two-dimensional hypersonic inlet

作　　者：张晓嘉[1] 梁德旺[1] 黄国平[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2008年第1期49-53,共5页Journal of Propulsion Technology

基　　金：国家"八六三"基金资助项目(2004AA723020)

摘　　要：对于二元高超声速进气道内压缩通道及隔离段设计,提出了进气道下壁弧形曲面构型方案。在一系列不同收缩比、不同波系配置的平面构型进气道基础上,通过基于N-S方程的数值模拟研究了不同半径的弧形过渡曲面对进气道性能的影响。发现采用弧形曲面过渡可以削弱平面构型方案对气流不必要的膨胀,减小隔离段进口处上侧壁面高压,改善隔离段进口气流均匀性。新构型有助于降低起动马赫数,且弧形过渡半径越大,收缩比越大,降低的程度越明显;还可以大大提高进气道的总压恢复,无须最后一道内压激波打在下壁面肩点上即可获得较高的性能。For design of internal contraction tunnel and isolator of two-dimensional hypersonic inlet, curved surface structure at the bottom wall was presented. Based on a series of plane surfaced hypersonic inlets with different internal contraction area ratios and different shocks, curved surface models with different radii were designed and simulated with N-S equation. Effects of are transition radius on inlet performances （e. g. temperature and pressure rise ratios, exit Mach number, total pressure recovery and starting Mach number） were investigated. The unnecessary expansion at the shoulder was weakened and the great local pressure at the isolator entrance was reduced as well as the flow at the entrance was more uniform. The startingup Mach number was decreased. The greater radius and internal contraction area ratio, the more decreased. The total pressure recovery was increased greatly by the new design. Even if without shock-on-shoulder, the inlet has better performance.

关 键 词：高超声速进气道 数值仿真 内压式进气道 隔离器 曲面 构型 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]