高超声速侧压式进气道溢流特性研究

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. 

Building and analysis of ontology based knowledge organizationmodel for aircraft engine design

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.