"Λ"型凸台对低隔道亚声速S弯进气道的流场控制研究
Research on Flow Field Control of"Λ"Type Step on Low Diverter Subsonic S-duct Inlet
唐小松 1金志光1
作者信息
- 1. 南京航空航天大学 能源与动力学院,江苏 南京 210016
- 折叠
摘要
针对某无人机进气系统低隔道亚声速S弯进气道出口流场畸变较大的问题,研究一种利用隔道内置"Λ"型凸台生成反向涡抑制出口畸变的流场控制手段.通过数值仿真分析"Λ"型凸台结构对抑制流场畸变的作用机制,给出不同来流条件下凸台结构参数对进气道出口总压恢复系数和流场畸变的影响规律.研究表明:畸变控制效果与凸台几何尺寸密切相关,合理设计的凸台对出口畸变抑制效果明显.
Abstract
Aimed at the large distortion of the flow field at the outlet of low diverter subsonic S-shaped inlet,a new control method for reducing outlet distortion by reverse vortices generated by"Λ"type step is studied.The mechanism of the suppression of flow field distortion by"Λ"type step is analyzed by numerical simulation,and the influence law of step structure parameters on the total pressure recovery and flow field distortion of the inlet outlet under different flow conditionsn is given.The research shows that the effect of suppressing distortion is closely related to the geometric size of the step,and the reasonably designed step has obvious improvement effect on the outlet distortion.
关键词
无人机/亚声速进气道/S弯进气道/流场畸变/流场控制/数值仿真Key words
unmanned aerial vehicle/subsonic inlet/S-duct inlet/flow field distortion/flow field control/numerical simulation引用本文复制引用
出版年
2024
国家科技期刊平台
NSTL
万方数据