空-空导弹用二元混压超声速进气道数值研究

Numerical study on flow field in 2-D segment compression supersonic intake for an air-to-air missile

对空空导弹固体火箭冲压发动机二元混压超声速进气道进行了数值研究。应用NND格式耦合对流迎风矢通量分裂技术 (AUSM) ,按照MacCormack时间分裂方法对贴体坐标系下二维雷诺平均N S方程进行有限差分离散。数值模拟了此进气道多种工况下的流动状态。结果表明 ,对于捕获激波和模拟附面层内流动均有很好的效果。在此基础上分析了来流马赫数、进气道工作高度及出口反压对进气道性能参数的影响。

A 2-D segment compression intake flow field was analyzed numerically.NND scheme and Advection Upstream Splitting Method(AUSM) were combined,and MacCormack time splitting method were applied to discrete the Reynold average Navier-Stokes equation in two-dimensional generalized coordinates with finite difference.By using this algorithm,the entire flow field was simulated for this supersonic intake, which was designed for an A-A missile solid propellant rocket ramjet(SPRR).Based on these numerical simulations,the effects of the coming flow Mach number,the working altitude and the back pressure of outlet on the primary performance parameters of this supersonic intake was analyzed.