Effects of suspension line on flow field around a supersonic parachute

Xiao Peng Xue; Hiroto Koyama; Yoshiaki Nakamura; Chih-yung Wen

doi:10.1016/j.ast.2015.02.014

Effects of suspension line on flow field around a supersonic parachute

Xiao Peng Xue, Hiroto Koyama, Yoshiaki Nakamura, Chih-yung Wen

Research output: Journal article publication › Journal article › Academic research › peer-review

32 Citations (Scopus)

Abstract

Numerical simulations based on a simple "immersed boundary technique" are performed to investigate the effects of suspension lines on the flow field around a three-dimensional rigid supersonic parachute mode consisting of a capsule and a canopy. The computational results show that the flow field has an unsteady pulsating characteristic. Furthermore, it is shown that the suspension lines prompt the formation of shock waves around them, which subsequently interact with the wake from the capsule and the canopy shock system. A good qualitative agreement is observed between the numerical results and experimental data.

Original language	English
Pages (from-to)	63-70
Number of pages	8
Journal	Aerospace Science and Technology
Volume	43
DOIs	https://doi.org/10.1016/j.ast.2015.02.014
Publication status	Published - 1 Jan 2015

Keywords

Immersed boundary technique
Numerical simulation
Supersonic parachute
Suspension line

ASJC Scopus subject areas

Aerospace Engineering

More information

10.1016/j.ast.2015.02.014

Cite this

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AU - Xue, Xiao Peng

AU - Koyama, Hiroto

AU - Nakamura, Yoshiaki

AU - Wen, Chih-yung

PY - 2015/1/1

Y1 - 2015/1/1

N2 - Numerical simulations based on a simple "immersed boundary technique" are performed to investigate the effects of suspension lines on the flow field around a three-dimensional rigid supersonic parachute mode consisting of a capsule and a canopy. The computational results show that the flow field has an unsteady pulsating characteristic. Furthermore, it is shown that the suspension lines prompt the formation of shock waves around them, which subsequently interact with the wake from the capsule and the canopy shock system. A good qualitative agreement is observed between the numerical results and experimental data.

AB - Numerical simulations based on a simple "immersed boundary technique" are performed to investigate the effects of suspension lines on the flow field around a three-dimensional rigid supersonic parachute mode consisting of a capsule and a canopy. The computational results show that the flow field has an unsteady pulsating characteristic. Furthermore, it is shown that the suspension lines prompt the formation of shock waves around them, which subsequently interact with the wake from the capsule and the canopy shock system. A good qualitative agreement is observed between the numerical results and experimental data.

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KW - Numerical simulation

KW - Supersonic parachute

KW - Suspension line

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SP - 63

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JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

ER -

Effects of suspension line on flow field around a supersonic parachute

Abstract

Keywords

ASJC Scopus subject areas

More information

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