前缘对进气道性能影响的数值模拟  

Numerical simulation of effects of leading edge on the performance of inlet

作　　者：王晓栋[1] 乐嘉陵[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《推进技术》2002年第6期460-462,共3页Journal of Propulsion Technology

基　　金：国家自然科学基金(19889209);航天高技术青年科学基金资助项目(863-2.98.7)

摘　　要：应用质量平均的N—S方程和B—L代数湍流模型,在不同压缩面前缘半径条件下,对高超声速进气道的 流场进行了数值模拟,对比研究了进气道压前缘半径对流场结构及性能的影响。在计算过程中,对方程中的对流项 采用了空间为二阶精度的TVD格式,扩散项则采用了二阶中心差分离散。The flow fields of a hypersonic inlet on the condition of different radius of compressing leading edge were simulated numerically by using the Favre-Averaged Navier-Stokes equations with the Baldwin-Lomax algebraic turbulence model. During the simulation, the effect of radius of the leading edge on the flow fields and the performance of the inlet were investigated comparatively. The second order Yee H C TVD scheme is used for the inviscid flux terms and a central difference considering the character of flow is used for the diffusion terms.

关 键 词：前缘 高超声速进气道 流动分布 数值仿真 纳维尔-斯托克斯方程 飞行器 

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]