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On-line Access: 2022-06-24

Received: 2021-10-21

Revision Accepted: 2022-01-04

Crosschecked: 2022-06-24

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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.6 P.479-494


Design method for hypersonic bump inlet based on transverse pressure gradient

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 bump inlet, Transverse pressure gradient (TPG), Boundary layer flow, Total pressure recovery, Starting ability, Mass flow correction

Shang-cheng XU, Yi WANG, Zhen-guo WANG, Xiao-qiang FAN, Bing XIONG. Design method for hypersonic bump inlet based on transverse pressure gradient[J]. Journal of Zhejiang University Science A, 2022, 23(6): 479-494.

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publisher="Zhejiang University Press & Springer",

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%T Design method for hypersonic bump inlet based on transverse pressure gradient
%A Shang-cheng XU
%A Zhen-guo WANG
%A Xiao-qiang FAN
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%P 479-494
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%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A2100532

T1 - Design method for hypersonic bump inlet based on transverse pressure gradient
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
IS - 6
SP - 479
EP - 494
%@ 1673-565X
Y1 - 2022
PB - Zhejiang University Press & Springer
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DOI - 10.1631/jzus.A2100532

transverse pressure gradient (TPG) is one of the key factors influencing the boundary layer airflow diversion in a bump inlet. This paper proposes a novel TPG-based hypersonic bump inlet design method. This method consists of two steps. First, a parametric optimization approach is employed to design a series of 2D inlets with various compression efficiencies. Then, according to the prescribed TPG, the optimized inlets are placed in different osculating planes to generate a 3D bump inlet. This method provides a means to directly control the aerodynamic parameters of the bump rather than the geometric parameters. By performing this method to a hypersonic chin inlet, a long and wide bump surface is formed in the compression wall, which leads to good integration of the bump/inlet. Results show that a part of the near-wall boundary layer flow is diverted by the bump, resulting in a slight decrease in the mass flow but a significant improvement in the total pressure recovery. In addition, the starting ability is significantly improved by adding the bump surface. Analysis reveals that the bump has a 3D rebuilding effect on the large-scale separation bubble of the unstarted inlet. Finally, a mass flow correction is performed on the designed bump inlet to increase the mass flow to full airflow capture. The results show that the mass flow rate of the corrected bump inlet reaches up to 0.9993, demonstrating that the correction method is effective.




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


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