摘要
进气道的起动能力决定着冲压发动机可能的工作范围,针对由于来流马赫数引起的进气道不起动现象,采用CFD技术开展了高超声速二维进气道起动与不起动过程的数值计算,并检验了一种改善进气道起动性能的边界层抽吸法。结果表明,进气道不起动的主要原因是非定常过程引起的内收缩段边界层分离和分离激波,进气道性能变化的突跃点为起动和不起动的分界点,边界层抽吸可以明显改善进气道的起动性能。
Inlet start ability determines working scope of ramjet.For unstar phenomenon due to free stream Mach number,we have employed CFD technique to numerically study starting and unstarting process of hypersonic two-dimension inlet,and validated boundary layer bleed method to improve inlet starting performance.The results indicate that the main reasons for inlet unstart are boundary layer separation and induced shock caused by unsteady flow.Abrupt changes in inlet performance divide the start and unstart process....
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2007年第6期1482-1487,共6页
Journal of Astronautics
基金
国家自然科学重点基金(90505016)
关键词
进气道
起动特性
边界层抽吸
Inlet
Start characteristics
Boundary layer bleed
