摘要
激波边界层相互作用是高超声速飞行器面临的重大问题,激波入射到平板引起的边界层分离是其中最具代表性的一种。用加权的3阶ENN格式计算了小磁雷诺数近似的MHD方程,研究了MHD控制层流边界层分离的机理。数值结果显示,通过局部电离空气并施加洛伦兹力,能使分离点向下游移动,分离区尺寸减小,从而抑制和缓解由于激波-边界层相互作用而引起的分离。
Shock Wave-Boundary Layer Interactions （SWBLI） are crucial for hypersonic vehicle. Low magnetic Reynolds numbers MHD equations with weighted ENN scheme were solved to investigate the mechanism of MHD control on the boundary layer separation induced by shock wave. The results show that MHD could move the separation point downstream and diminish the separation bubble, and then alleviate or even finally eliminate the shock induced separation.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2009年第2期229-233,共5页
Journal of Propulsion Technology
基金
国家自然科学基金(90305022
10525212)
关键词
冲压喷气发动机
进气道
激波
边界层
边界层分离
Ramjet engine
Inlet
Shock wave
Boundary layer
Boundary layer separation
