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

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.