Numerical simulation of swirling flowfield in combustion chamber for hybrid rocket engine

Kazuki Yoshimura, Keisuke Sawada

研究成果: Conference contribution

9 被引用数 (Scopus)

抄録

A numerical simulation of swirling flowfield in combustion chamber for hybrid rocket engine is attempted by solving the Navier-Stokes equations using a high order accurate Weighted Compact Nonlinear Scheme with accounting for a single stage reaction model. When chemical reactions are ignored, there appears a reverse flow region resulting in a threefold co-axial swirling structure in the combustion chamber. Detailed structure of the swirling flowfield is described. The result of the preliminary calculation for the combustion case is also given in which combustion is shown to occur in the boundary layer region.

本文言語English
ホスト出版物のタイトル48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
出版社American Institute of Aeronautics and Astronautics Inc.
ISBN(印刷版)9781600867392
DOI
出版ステータスPublished - 2010

出版物シリーズ

名前48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

ASJC Scopus subject areas

  • 航空宇宙工学

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