首页 | 本学科首页   官方微博 | 高级检索  
     检索      

高超声速侧压式模型进气道不起动特性分析
引用本文:袁化成,梁德旺.高超声速侧压式模型进气道不起动特性分析[J].南京航空航天大学学报,2004,36(6):683-687.
作者姓名:袁化成  梁德旺
作者单位:南京航空航天大学能源与动力学院,南京,210016
基金项目:国家 8 63高技术研究发展计划 (2 0 0 3 AA72 3 0 2 0 )资助项目
摘    要:对某典型高超声速侧压式进气道三维流场进行了数值分析,就壁面压力分布、波系结构和近壁流谱图与实验结果进行了比较,计算反映了流动的基本特征。分析了在不同来流马赫数下的流动特征,随着来流马赫数的减小,激波角增大,压缩波在通道内的反射次数增加,而强度逐渐减弱,总压恢复系数逐渐增大。当马赫数减小到一定数值时,在等直隔离段入口出现喉道截面,进一步减小来流马赫数,流量阻塞,引起压力升高,波系向进口方向移动,波后出现亚声速流场,进气道不起动。同时还发现当不起动现象发生时,由于波后分离包的存在,在进气道的进口前形成向后倾斜的激波而不是正激波。本文还提出了一种确定不起动马赫数的方法。

关 键 词:高超声速侧压式进气道  不起动  数值模拟
文章编号:1005-2615(2004)06-0683-05
修稿时间:2004年6月14日

Characteristic Analysis of Unstart Performance for Hypersonic Side-Wall Inlet Model
YUAN Hua-cheng,LIANG De-wang.Characteristic Analysis of Unstart Performance for Hypersonic Side-Wall Inlet Model[J].Journal of Nanjing University of Aeronautics & Astronautics,2004,36(6):683-687.
Authors:YUAN Hua-cheng  LIANG De-wang
Abstract:The unstart phenomena is one of the most important issues in hypersonic inlets. The deep understand for the unstart phenomena is very important to the design of hypersonic inlets. The flow in a typical hypersonic side-wall inlet is analyzed with a three-dimensional numerical analyer. The wall pressure distribution, the shock structure and flow patterns near wall of the hypersonic side-wall inlet are compared with experimental data. Result shows that the numerical results have represented the basic flow characteristics. The flow characteristics of the inlet at different Mach numbers of inflow are also discussed. With the decrease of Mach number of inflow, the total pressure recovery and the shock angle increase; the number of reflection of shock wave in the duct also increases, but the strength of the shock wave decreases. A throat section appears at the entrance of the isolator with equal area and the flow is choked. Finally, the pressure become very high immediately and a unstart phenomena appears. When the inlet unstarted, there is a inclined backward shock in the front of the inlet due to the existence of separation bubble behind the shock near the wall. The method for the unstart Mach number is described.
Keywords:hypersonic side-wall inlet  unstart  numerical simulation
本文献已被 CNKI 维普 万方数据 等数据库收录!
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号