高超进气道临界起动特征  

Critical starting characteristics of hypersonic inlets

作　　者：王成鹏[1] 程克明[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《航空动力学报》2008年第6期997-1002,共6页Journal of Aerospace Power

基　　金：国家自然科学基金(10702029;90716013);航空科学基金(2006ZB52013)

摘　　要：通过对一种吸气式高超飞行器模型的Ma=7风洞吹风试验结果的分析,获得了高超进气道不起动、临界起动和起动状态的流动特征,包括流动图谱、压力分布和气动力分布;并将进气道内收缩比值与等熵理论最大起动收缩比限、自起动最大起动收缩比限和经验最大起动收缩比限做了对比分析,分析结果有助于高超进气道的设计和起动性能的评估.An airbreathing hypersonic vehicle model was tested in the Ma=7 wind tunnel. The experimental face p tions. ressure measure investigations yielded schl ments along inlet/internal ieren pictures of the inlet flow, static sur flowpath and The flow field characteristics were achieved, such as. aerodynamic force distribu unstarting hypersonic inlet, critical starting and starting condition. The ability of isentropic limit, Kantrowitz limit and Van Wie limit to predict the starting contraction ratio was assessed, showing that the isentropic limit and Van Wie limit could not estimate the allowable starting and maximum contraction ratio. The Kantrowitz limit is slightly conservative. The above results are helpful to the design of the hypersonic inlet and the assessment of starting performance.

关 键 词：航空 航天推进系统 吸气式高超飞行器 进气道 起动 风洞试验 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]