高焓激波风洞自由流参数测量的数值重建  

Numerical rebuilding of free stream measurement in the high enthalpy shock tunnel

作　　者：曾明[1] 林贞彬[2] 郭大华[2] 柳军[1] 瞿章华[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073 [2]中国科学院力学研究所高温气体动力学重点实验室,北京100080

出　　处：《空气动力学学报》2009年第3期358-362,共5页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目(10672170,10502056)

摘　　要：高焓风洞中参数测量本身受到高温非平衡效应影响,单纯依靠实验测量不足以确定详细的风洞自由流参数。本文以JF-10高焓激波风洞为背景,通过喷管-试验段-测量仪模型非平衡流场的连贯计算,开展自由流参数测量的数值重建。在比较分析测量仪模型绕流场的计算结果和实验测量值的基础上,结合喷管流场的数值模拟结果,共同确定高焓风洞的详细自由流参数。It is difficult to determine the simulative parameters of a new high enthalpy tunnel merely by measurements because the measurements themselves are affected by the high temperature nonequilbrium effects. Taking the high enthalpy shock tunnel JF-10 as an example, the free-stream measurements taken in the test section are numerically rebuilt through calculating the nozzle flow field and the flow fields around the measurement probes sequentially. The detail free-stream properties in JF-10 tunnel are determined by integrating the numerical solution of the nozzle flow field with the free-stream measurement values and the results of the numerical rebuilding of the measurements.

关 键 词：高焓激波风洞 高超声速喷管 数值重建 非平衡流 

分 类 号：O242[理学—计算数学]