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

Kazuki Yoshimura, Keisuke Sawada

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

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.

Original languageEnglish
Title of host publication48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781600867392
DOIs
Publication statusPublished - 2010

Publication series

Name48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

ASJC Scopus subject areas

  • Aerospace Engineering

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