摘要
对吸气式高超声速飞行器而言,内流道的流态对推进系统乃至飞行器的工作特性有重要影响。本文用风洞实验的方法研究了升力体(类X-43)、二元进气道和轴对称进气道三种构型在不同来流、内部几何和燃烧室反压条件下的内流道工作情况,着重分析了起动/不起动状态对内流道流动特征及全机气动力的影响,提出并发展了通过在燃烧室内喷射高压气流的内流道反压模拟技术,并运用这一技术成功实现了内流道由起动向不起动、由不起动向起动/再起动的切换。
Based on the research background of the effect of the hypersonic airframe/propulsion system integrative research coupling with the inlet, with three-airbreathing hypersonic aircraft/flow model （a base model configuration, a sort of 2D inlet modal, an axisymmetric hypersonic vehicle） for the integrative of research object, the paper studies the flow characteristics and shock wave structure of inlet/inner flowpath and inlet start characteristics responsing to concerning factors, under different flowing, geometry and combustion chamber back pressure condition. Especially, the paper concerns the influence of the combustion chamber with jet high-pressure air flow on inlet for inlet start, inlet unstart and automatic start, which simulates the environmental pressure generated from combustion products, and the features of hypersonic full flowpath flowing and the influence on aerodynamic characteristics.
出处
《空气动力学学报》
EI
CSCD
北大核心
2009年第2期193-198,共6页
Acta Aerodynamica Sinica
基金
国防科工委基础预研项目(A2520060219)
国家自然科学基金(10572059)
