摘要
首先介绍了高超声速侧压式进气道的构型,定义了侧压式进气道可能存在的两种溢流模态———构型溢流和压差溢流;然后对构型溢流进行了理论分析和计算,阐明了侧板后掠的侧压进气道设计参数对构型溢流影响;最后对不同侧板配置方式的侧压式进气道进行了数值模拟,通过对比分析发现由唇口板位置所决定的溢流窗大小对进气道溢流特性的影响显著.
Firstly configurations of the generic sidewall compression scramjet inlets were introduced and then two kinds of spillage that sidewall compression inlets might occur were introduced. Spillage induced by the back-swept sidewall leading edge is called Configuration Spillage, while spillage evoked by the pressure difference is described as Pressure-Driven Spillage. Parametric analysis of the inviscid effects of leading edge sweep, sidewall compression, width-height ratio, cowl position and inflow Mach number on spillage was carried out. Finally, numerical simulations were performed for a series of inlets at various flight altitude and speed. The research indicates that the area of spillage window, which is mainly determined by the position of the cowl, significantly influences the spillage characteristics of the scramjet inlet.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第1期85-89,共5页
Journal of Aerospace Power
基金
国家863计划资助项目
关键词
航空、航天推进系统
高超声速
进气道
侧压
溢流特性
数值模拟
aerospace propulsion system
hypersonic
inlet
sidewall compression
spillage characteristics
numerical simulation
