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On-line Access: 2022-10-20

Received: 2022-03-23

Revision Accepted: 2022-08-01

Crosschecked: 2022-10-21

Cited: 0

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Citations:  Bibtex RefMan EndNote GB/T7714


Shang-cheng XU




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Journal of Zhejiang University SCIENCE A 2022 Vol.23 No.10 P.807-819


Effects of bump parameters on hypersonic inlet starting performance

Author(s):  Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG

Affiliation(s):  College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China

Corresponding email(s):   wange_nudt@163.com

Key Words:  Hypersonic inlet, Bump, Boundary layer flow, Starting performance, Large-scale separation bubble

Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG. Effects of bump parameters on hypersonic inlet starting performance[J]. Journal of Zhejiang University Science A, 2022, 23(10): 807-819.

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author="Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG",
journal="Journal of Zhejiang University Science A",
publisher="Zhejiang University Press & Springer",

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%T Effects of bump parameters on hypersonic inlet starting performance
%A Shang-cheng XU
%A Zhen-guo WANG
%A Xiao-qiang FAN
%J Journal of Zhejiang University SCIENCE A
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%@ 1673-565X
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%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A2200155

T1 - Effects of bump parameters on hypersonic inlet starting performance
A1 - Shang-cheng XU
A1 - Yi WANG
A1 - Zhen-guo WANG
A1 - Xiao-qiang FAN
A1 - Bing XIONG
J0 - Journal of Zhejiang University Science A
VL - 23
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SP - 807
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%@ 1673-565X
Y1 - 2022
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A2200155

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.




Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article


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