物理学报Issue(20)：1-8,8.DOI:10.7498/aps.63.204701
来流边界层效应下斜坡诱导的斜爆轰波
Ramp-induced oblique detonation wave with an incoming b oudary layer effect
摘要
Abstract
The behavior of reacting shock wave in supersonic premixed flow with the effect of incoming boundary layer is investigated experimentally. A supersonic premixed flow at a Mach number of 3 encounters a ramp, and an oblique detonation wave (ODW) is produced. Four ramp angles (θ) are designed from 36◦ to 45◦ (interval of 3 degree) and the equivalence ratio (Φ) can be varied. At a lower equivalence ratio, the ODW cannot be initiated and instead the shock-induced combustion (SIC) comes into being. It is discovered that the overall flow field presents more significant unsteadiness for SIC than for inert shock wave because the separation region is greatly enlarged for SIC due to heat release by chemical reactions in the separation region. As for the ODW, it is prone to propagating upstream after initiated for current experimental conditions. For 39◦ ramp, the separation region of boundary layer is relatively small, and the ODW presents an abrupt pattern for which a transverse wave exists. However, larger separation region for 42◦ramp and its unsteadiness make the transverse wave intermittently appear. For 45◦ ramp, the even larger separation region makes the transverse wave thoroughly disappear and the ODW presents a smooth pattern.关键词
斜爆轰波/激波诱导燃烧/边界层分离/非定常性Key words
oblique detonation wave/shock-induced combustion/boundary layer separation/unsteadiness引用本文复制引用
刘彧,周进,林志勇..来流边界层效应下斜坡诱导的斜爆轰波[J].物理学报,2014,(20):1-8,8.基金项目
国家自然科学基金(批准号:91016028,91216121)资助的课题.* Project supported by the National Natural Science Foundation of China (Grant Nos.91016028,91216121) （批准号:91016028,91216121）
