超声速进气道湍流流场的数值模拟  

NUMERICAL SIMULATION OF TURBULENT FLOW FIELD SUPERSONIC INLET

作　　者：赵桂萍[1] 周新海[2] 

机构地区：[1]中国科学院力学所 [2]西北工业大学航空动力与热力工程系

出　　处：《推进技术》1998年第3期33-38,共6页Journal of Propulsion Technology

摘　　要：采用有限体积法数值模拟了超声速进气道的湍流流场，改进了离散纳维尔－斯托克斯方程中粘性项的方法，使之具有较好的守恒性，研究使用了变系数的隐式残差光顺等加速收敛技术，并讨论了超音来流、收敛型进气道复杂流场初场的给定方法，所得到的数值解正确地展示了流场的复杂激波结构。A numerical analysis method of threedimensional compressible viscous flow of rectangular supersonic inlet for Hypersonic Ramjet Engine (HRE) was studiedThe major characteristics of this kind of inlet are:ployshock wave structure,boundary layershock wave interaction,and second flow existing in the flow field at same timeThe method is based on Jameson's finite volume schemeIn stead of difference method,an integral scheme is adapted to disperse the viscous terms of NavierStokes equations ensure the conservation of the schemeVarying coefficient implicit residual smoothing technique was studied to accelerate convergence The specified initial flow field and boundary condition for the supersonic convergence path was discussed

关 键 词：超声速 进气道 有限体积法 N-S方程 湍流流场 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]