STRUCTURE OF MIXING LAYER IN HIGH ENTHALPY HYPERSONIC FLOWS

高焓高超声速流混合层结构

基本信息

批准号：
07044116
负责人：
TAKAYAMA Kazuyoshi
金额：
$ 3.84万
依托单位：
Tohoku University
依托单位国家：
日本
项目类别：
Grant-in-Aid for international Scientific Research
财政年份：
1995
资助国家：
日本
起止时间：
1995 至 1997
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-07044116/
关键词：
shock wave hypersonic flow turbulent mixing nozzle flow real gas effect numerical simulation 自由ピストン衝撃波風洞スクラムジェットエンジン

项目摘要

Topics on hypersonic turbulent mixing are not only basic research topics of high speed gas dynamics but also important applications of shock wave research. This international joint research program has been carried out for three years under close sollaborations between the Shock Wave Research Center Institute of fluid Science and the Institute of Aerospace Studies University Toronto.Results so far obtained are summarized as following :(1) A mathematical modelling of hypersonic turbulent mixing has been obtained by establishing a finite difference scheme which can handle three-dimentional Navies-Stokes equations in unstructured grid systems.(2) In order to include the chemical reaction terms in the above mentioned numerical scheme, detailed elementary processes of hedrogen-oxygen reactions has been investigated.(3) In conjunction with understanding of elementary processes of hypersonic turbulent mixsing, the motion of shock waves and flows behing them has been investigated experimentall … More y and numerically.(4) The characteristic of a compact free piston shock tunnel and its contoured nozzle flow has investigated : piton motion in compression tube ; starting process of nozzle fow ; effect of diaphragm location on the nozzle flows ; Pitt pressure profile of nozzle flow ; driver gas contamination. Based upon these results, it is found that the contoured Mach 6 nozzle has a very limited working region so that a conical nozzle is designed for its replacement.(5) The stagnation enthalpy of 14 MA/kg and nozzle flow Mach number of 6 has been obtained. Double exposure holographic interferometric observation has been successfully applied to the flow over a cylinder.(6) The results have been obtained under close collaboration during the stay of Professor Jean Sislian for total 8 months from the fiscal years 1995 to 1997 and also the stay of Mr.Jurgen Schumacher for 6 month in 1997.(7) The results so far obtained are submitted for the publication in international journals having high reputation. Less

高超声速湍流混合课题不仅是高速气体动力学的基础研究课题，也是冲击波研究的重要应用，这一国际联合研究项目在冲击波研究中心流体科学研究所的密切配合下开展了三年。目前所取得的成果总结如下：(1)通过建立可处理三维空间的有限差分格式，得到了高超声速湍流混合的数学模型。非结构化网格系统中的Navies-Stokes方程。(2)为了将化学反应项包含在上述数值方案中，研究了氢氧反应的详细基本过程。(3)结合对高超声速湍流混合、冲击波及其后面的流动的运动已通过实验和数值研究。（4）研究了紧凑型自由活塞激波风洞及其轮廓喷嘴流的特性：压缩管中的活塞运动；喷嘴流的启动过程；喷嘴流的皮特压力分布；基于这些结果，发现轮廓马赫喷嘴具有非常大的影响。 (5)获得了14MA/kg的滞止热和6倍的喷嘴流量马赫数。曝光全息干涉观测已成功应用于圆柱体上的流动。(6) 该结果是Jean Sislian教授在1995年至1997财年总共8个月的逗留期间以及Mr.在逗留期间的密切合作下获得的。 .Jurgen Schumacher于1997年进行了6个月的研究。(7) 迄今为止所获得的成果已提交到具有较高声誉的国际期刊上发表。