南京理工大学学报（自然科学版）Issue(6)：891-895,5.
高超声速进气道流场的磁流体控制
Magnetohydrodynamic control of hypersonic inlet flow
摘要
Abstract
To numerically study the application of the local magnetohydrodynamic( MHD) control on hypersonic inlet flow,two dimensional Euler equations with MHD source terms are solved by using an explicit second order hybrid ROE/HLL scheme. The adaptive mesh refinement technique and immersed boundary method are adopted to handle the complex boundary. The MHD control processes of the scramjet inlet flow with double wedge are numerically simulated. The results show that the two oblique shock waves at the inlet can be controlled by the Lorentz force applied at the forebody of the first ramp,the positions of two oblique shock waves at the inlet can be controlled,and the directions of the Lorentz force have significant effects on the MHD control processes. The two oblique shock waves at off-design conditions can be restored to the desired location by a Lorentz force with proper magnitude and direction,but their flow field structures are slightly different.关键词
高超声速进气道/流场/磁流体控制/超燃冲压发动机/洛伦兹力Key words
hypersonic inlet/flow/magnetohydrodynamic control/scramjet/Lorentz force分类
数理科学引用本文复制引用
孙晓晖,陈志华,薛大文..高超声速进气道流场的磁流体控制[J].南京理工大学学报（自然科学版）,2013,(6):891-895,5.基金项目
江苏省2011年度普通高校研究生科研创新计划(CXZZ11_0233) （CXZZ11_0233）
