航空学报2025，Vol.46Issue(24)：22-35,14.DOI:10.7527/S1000-6893.2025.32314
背负式进气道典型气动特性及流动机理
Typical aerodynamic characteristics and flow mechanisms of dorsal inlet
摘要
Abstract
Numerical simulations were conducted to investigate the flow characteristics and flow formation mechanism of a typical layout of dorsal binary curved compression inlet at different angles of attack.The results show that the flow coefficient of the inlet and the total pressure recovery coefficient of the throat decrease simultaneously with the increase of the angle of attack,and the flow coefficient decreases by 24.4%and the total pressure recovery coefficient de-creases by 14.8%when the angle of attack increases from 0° to 10°.The boundary layer diverter can effectively im-prove the flow coefficient and total pressure recovery coefficient of the inlet channel,the flow coefficient increases by about 4%,and the total pressure recovery coefficient of the throat channel increases by about 0.02.The analysis of the study shows that,with the increase of the angle of attack of the flight,the masking effect of the forebody on the dorsal inlet induces the appearance of the forebody expansion wave,which causes the acceleration of the airflow in front of the inlet.The higher Mach number and uneven distribution in front of the inlet are the main reasons for the si-multaneous decrease of the flow coefficient and the total pressure recovery coefficient.Accordingly,a theoretical model of the flow characteristics of the forebody/inlet for this type of dorsal layout is established,which reveals the lin-ear correlation between the Mach number in front of the inlet and the angle of attack,which can be used to predict the flow characteristics of the inlet accordingly.By changing the relative position of the inlet along the flow direction in the forebody,the influence of the boundary layer on the inlet flow can be improved,and the flow coefficient and total pres-sure recovery coefficient can be enhanced,but the enhancement is limited due to the fact that the Mach number in front of the inlet is still high and unevenly distributed.关键词
背负式进气道/边界层隔道/流量系数/攻角特性/膨胀波/线性关系Key words
dorsal inlet/boundary layer diverter/flow coefficient/angle of attack characteristic/expansion waves/linear relationship分类
航空航天引用本文复制引用
YANG Shanchao,LONG Hongyin,YUAN Huacheng..背负式进气道典型气动特性及流动机理[J].航空学报,2025,46(24):22-35,14.基金项目
国家自然科学基金(12302299) （12302299）
冲压发动机技术全国重点实验室基金(2023-JCJQ-LB-018-007) National Natural Science Foundation of China(12302299) （2023-JCJQ-LB-018-007）
National Key Laboratory Foundation of Ramjet(2023-JCJQ-LB-018-007) （2023-JCJQ-LB-018-007）
