前缘对进气道性能影响的数值模拟

推进技术 ›› 2002, Vol. 23 ›› Issue (6): 460-462.

前缘对进气道性能影响的数值模拟

王晓栋,乐嘉陵

中国空气动力研究与发展中心四川绵阳 621000;中国空气动力研究与发展中心四川绵阳 621000

发布日期:2021-08-15
基金资助:
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)

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

China Aerodynamics Research and Development Center, Mianyang 621000, China;China Aerodynamics Research and Development Center, Mianyang 621000, China

Published:2021-08-15

摘要/Abstract

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。

关键词: 高超声速进气道;流动分布;数值仿真;纳维尔-斯托克斯方程

Abstract: 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.

Key words: Hypersonic inlet;Flow distribution;Numerical simulation;Navier-Stokes equations

王晓栋,乐嘉陵. 前缘对进气道性能影响的数值模拟[J]. 推进技术, 2002, 23(6): 460-462.