开启式高超声速进气道启动性能试验

基金项目: 国家863计划

Experimental investigation on the starting characteristics of a hypersonic inlet with moving entrance door

Institute of Aerospace and Material Engineering, National University of Defense Technology, Changsha 410073, China

摘要: 设计了具有入口开启功能的高超声速进气道,并在Ma=6连续式自由射流风洞中进行了启动性能的试验研究.通过对进气道壁面静压变化和捕获流量的测量,验证了此种具有开启功能的变几何方案的可行性.试验结果表明,开启机构能够有效地提高进气道的启动性能.分析认为,进气道入口的逐渐打开过程辅助进气道建立起超声速流场.同时,开启机构避免了进气道自启动的迟滞效应,使进气道实现启动.
- 航空、航天推进系统 /
- 高超声速进气道 /
- 变几何 /
- 启动性能 /
- 自由射流实验
Abstract: A three dimensional hypersonic inlet with moving entrance door was designed and tested in the Ma=6 free-jet wind tunnel to investigate the starting characteristics.This variable geometry design was testified to be a feasible way to accomplish the entrance opening process of the inlet.The results reveal that the moving entrance door can effectively improve the starting ability of the inlet.The gradually opening process could assist the inlet in starting and also avoid the hysteretic effect of the inlet selfstart.
- aerospace propulsion system /
- hypersonic inlet /
- variable geometry /
- starting characteristics /
- free-jet experiment

[1]	Hass N E,Smart M K,Paull A.Flight data analysis of HyShot 2[R].AIAA 2005-3354.
[2]	Huebner L D,Rock K E,Ruf E G,et al.Hyper-X flight engine ground testing for X-43 flight risk reduction[R].AIAA 2001-1809.
[3]	Tahir R B,Molder S,Timofeev E V.Unsteady starting of high Mach number air inlets-A CFD study[R].AIAA 2003-5191.
[4]	Barber T J,Hiett D,Fastenberg S.CFD modeling of the hypersonic inlet starting problem[R].AIAA 2006-123.
[5]	Van Wie D M,Kwok F T,Walsh R F.Starting characteristics of supersonic inlets[R].AIAA 96-2914.
[6]	Hagenmaier M A,Tam C J,Chakravarthy S.Study of moving start door flow physics for scramjet[R].AIAA 99-4957.
[7]	范晓樯.高超声速进气道的设计、计算与实验研究[D].长沙:国防科技大学研究生院,2006.FAN Xiaoqiang.Design method,numerical simulation and experimental research of hypersonic inlet[D].Changsha:Doctoral Thesis of Engineering,National University of Defense Technology,2006.