高超声速进气道流场的磁流体控制  

Magnetohydrodynamic control of hypersonic inlet flow

作　　者：孙晓晖[1] 陈志华[1] 薛大文[1] 

机构地区：[1]南京理工大学瞬态物理国家重点实验室,江苏南京210094

出　　处：《南京理工大学学报》2013年第6期891-895,共5页Journal of Nanjing University of Science and Technology

基　　金：江苏省2011年度普通高校研究生科研创新计划(CXZZ11_0233)

摘　　要：为对磁流体(MHD)控制在高超声速进气道流场的应用进行数值研究,利用二阶精度的混合ROE/HLL格式对二维带MHD电磁源项的欧拉方程进行求解。采用自适应网格加密技术,并结合沉浸边界法对复杂外形的边界问题进行处理。数值模拟了超燃冲压发动机双楔形进气道流场的MHD控制过程。计算结果表明:应用在弹丸头部第一道斜劈的洛伦兹力可以控制外进气道上的两道斜激波。洛伦兹力的方向对MHD控制的效果具有重要影响。大小和方向适合的洛伦兹力可以同时将非设计情况下的两道斜激波恢复到设计位置,但流场情况会稍有不同。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 

分 类 号：N55[自然科学总论]