二维超燃冲压发动机磁控进气道的数值模拟  

Numerical simulation of a two-dimensional scramjet MHD controlled inlet

作　　者：郑小梅[1] 吕浩宇[1] 徐大军[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《推进技术》2010年第1期12-17,共6页Journal of Propulsion Technology

基　　金：国家"八六三"高技术发展计划

摘　　要：针对飞行马赫数大于设计马赫数的情况,采用二维磁流体动力学方程对磁控进气道进行了数值模拟研究。数值模拟结果表明磁流体装置的电磁作用可以使非设计马赫数下进气道激波满足SOL(shock on lip)条件,并使出口处的流动变得均匀。分析了磁流体作用位置、宽度和深度等关键控制参数对该类进气道性能的影响,计算结果表明,磁流体作用区域越靠近飞行器前缘,而且在纵向越深,则进气道出口处的流动越均匀,但流率会有所下降;若磁流体作用区域较宽,则需较小的磁场就能使非设计马赫数下进气道的激波结构满足SOL条件。Two-dimensional inviscid steady-state flow equations coupled with MHD effects are solved jointly with MHD equations to study the performance of an MHD controlled inlet when flight Maeh number is larger than the design value. At a proper choice of parameters the shocks are moved back to the cowl lip, and the outlet parameters became evener. The influenee of the MHD interaction loeation, width and depth to the MHD controlled inlet has been analyzed, the calculations show that in order to make the outlet flow evener the MHD region should be placed upstream and penetrate into the flow deeper. With a wider MHD interaction region, smaller magnitude of the magnetic induction is needed to move the shocks back to the cowl lip.

关 键 词：超燃冲压发动机 磁流体动力学 磁控进气道 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]