Abstract: Three-dimensional turbulent flows in a 2-D mixed-compression supersonic intake of an A-A missile were simulated numerically under uniform and non-uniform coming flow condition. On the base of the MacCormack time splitting method, NND scheme, Advection Upstream Splitting Method(AUSM) and the Baldwin-Lomax turbulent model were applied to discrete the Reynold average Navier-Stokes equation in three-dimensional generalized coordinates with finite difference. And then, the variations of primary performance parameters of this supersonic intake with the flight Mach number, the flying altitude, attack-angle of the missile and the back pressure of the outlet were analyzed, which might be useful to study the supersonic intake deeply.

Key words: Supersonic inlet;Mixed compression inlet;Numerical simulation;NND scheme;Vector splitting

摘要： 按照MacCormack时间分裂方法 ,应用NND格式、对流迎风矢通量分裂 (AUSM)技术和Baldwin Lomax混合长度代数湍流模型 ,对贴体坐标系下三维雷诺平均N S方程进行有限差分离散。数值计算了均匀来流和非均匀来流条件下二元混压超声速进气道三维湍流流动状态 ,分析了该进气道主要性能参数随出口反压、来流马赫数、导弹工作高度及飞行攻角的变化特性 ,为深入研究进气道性能提供了一定辅助手段。

关键词: 超声速进气道;混合压缩式进气道;数值模拟;NND格式;矢通量分裂