Unstart is an unwanted flow phenomenon in a hypersonic inlet. When an unstart occurs, the captured airflow flowing through the engine significantly decreases with strong unsteady characteristics, which may lead to thrust loss or even combustor flameout. In this study, various bump configurations were designed to be integrated with a hypersonic inlet to improve its starting ability. A bump was defined as an integrated 3D compression surface installed upstream of the inlet entrance. The starting processes of these bump inlets were numerically simulated to investigate the effect laws and flow mechanisms of the bump parameters. Tests on bump height revealed that the starting performance could be significantly improved by increasing bump height, with the starting Mach number decreasing by 0.55 for the inlet with the highest bump. The high bump facilitates the side movement of the subsonic flow in the separation zone, which leads to a small separation bubble, thus accelerating the starting process. Further, the starting ability can be improved by designing a relatively wide bump, which results in a decline in the starting Mach number by 0.44. When the bump has the same or greater width compared with the airflow capture range, a growing spillage along the transverse direction can be formed so that the airflow in the separation bubble can be easily excluded, improving the starting ability.

Shang-cheng XU;Yi WANG;Zhen-guo WANG;Xiao-qiang FAN;Bing XIONG

College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China

浙江大学学报（英文版）（A辑：应用物理和工程）

[1]Shang-cheng XU;Yi WANG;Zhen-guo WANG;Xiao-qiang FAN;Bing XIONG-.Effects of bump parameters on hypersonic inlet starting performance)[J].浙江大学学报（英文版）（A辑：应用物理和工程）,2022(10):807-819

Unstart,flameout,spillage

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