航空科学技术2025，Vol.36Issue(3)：78-85,8.DOI:10.19452/j.issn1007-5453.2025.03.010
长机身埋入式进气道流场控制仿真研究
Simulation Study of Flow Field Control on the Submerged Inlet with Long Fuselage
王利平 1马高建 1孙振华 1李艳福2
作者信息
- 1. 中国空空导弹研究院,河南 洛阳 471009
- 2. 中国人民解放军93160部队,北京 100076
- 折叠
摘要
Abstract
To enhance stealth capacity,a signifcant number of UVAs utilize submerged inlet,however,when the fuselage length is relatively long,it can substantially degrade the performance of inlet.On the basis of a structural model of long fuselage and tail submerged inlet,in order to solve the problem of low performance caused by low energy airflow on the long fuselage entering the inlet,a flow field control scheme of adding a vortex generator group on the surface of the front fuselage of the inlet was adopted.The influence of vortex generator design parameters on inlet port performance was analyzed,and a set of turbulence design parameters was optimized,and the performance improvement effect of the inlet was obtained.The simulation results show that,chord spacing S1,length S2,height H,deflection angle δ and length L from inlet of the vortex generator have some improvement on the performance of the submerged inlet.Compared with the original inlet was obtained,the total pressure recovery coefficient is increased by 1.1%and distortion index|DC60|is reduced by 22.7%,thus effectively improved the flow field quality of entering the aircraft engine.关键词
埋入式进气道/涡流发生器/总压恢复系数/畸变指数Key words
submerged inlet/vortex generator/total pressure recovery coefficient/distortion index引用本文复制引用
王利平,马高建,孙振华,李艳福..长机身埋入式进气道流场控制仿真研究[J].航空科学技术,2025,36(3):78-85,8.
