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 publicationJournal articleAcademic researchpeer-review

28 Citations (Scopus)


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 languageEnglish
Pages (from-to)63-70
Number of pages8
JournalAerospace Science and Technology
Publication statusPublished - 1 Jan 2015


  • Immersed boundary technique
  • Numerical simulation
  • Supersonic parachute
  • Suspension line

ASJC Scopus subject areas

  • Aerospace Engineering


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