CLC number: V423
On-line Access: 2024-08-27
Received: 2023-10-17
Revision Accepted: 2024-05-08
Crosschecked: 2020-07-15
Cited: 0
Clicked: 3028
Bin-xian Shen, Hong-peng Liu, Wei-qiang Liu. Influence of angle of attack on a combined opposing jet and platelet transpiration cooling blunt nose in hypersonic vehicle[J]. Journal of Zhejiang University Science A, 2020, 21(9): 761-769.
@article{title="Influence of angle of attack on a combined opposing jet and platelet transpiration cooling blunt nose in hypersonic vehicle",
author="Bin-xian Shen, Hong-peng Liu, Wei-qiang Liu",
journal="Journal of Zhejiang University Science A",
volume="21",
number="9",
pages="761-769",
year="2020",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A1900514"
}
%0 Journal Article
%T Influence of angle of attack on a combined opposing jet and platelet transpiration cooling blunt nose in hypersonic vehicle
%A Bin-xian Shen
%A Hong-peng Liu
%A Wei-qiang Liu
%J Journal of Zhejiang University SCIENCE A
%V 21
%N 9
%P 761-769
%@ 1673-565X
%D 2020
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A1900514
TY - JOUR
T1 - Influence of angle of attack on a combined opposing jet and platelet transpiration cooling blunt nose in hypersonic vehicle
A1 - Bin-xian Shen
A1 - Hong-peng Liu
A1 - Wei-qiang Liu
J0 - Journal of Zhejiang University Science A
VL - 21
IS - 9
SP - 761
EP - 769
%@ 1673-565X
Y1 - 2020
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A1900514
Abstract: Flying condition with angle of attack is inevitable in a hypersonic vehicle, and it may influence the thermal protection system (TPS) performance of opposing jet and its combinations. A 3D Navier–Stokes equation and shear stress transfer (SST) k-ω model with compressible correction are employed to simulate the angle of attack characteristics of a blunt body with opposing jet and platelet transpiration TPS. The flowfield and heat flux transfer for angles of attack 0°, 3°, 6° with jet pressure ratio PR=0.1 and 0°, 6°, 12° with PR=0.2 are obtained. Numerical results show that the flowfield is no longer symmetrical with the effect of the angle of attack. The flowfield and heat transfer in windward and leeward performed adversely. The recompression shock wave in windward is strengthened, which increases local temperature and strengthens heat transfer. The opposing jet fails in thermal protection when the angle of attack reaches critical value; however, the critical angle of attack can be promoted by increasing PR. Finally, the transpiration gas can strengthen the cooling efficiency of windward, thereby, increasing the critical angle of attack.
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