Numerical analysis of turbulent combustion flow in HyShot scramjet combustor

Su Hee Won, In Seuck Jeung, Jeong Yeol Choi, Vigor Yang, Fuhua Ma

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

Abstract

This paper describes numerical efforts to investigate combustion characteristics of HyShot scramjet combustor, where gaseous hydrogen is transversely injected into a supersonic cross flow. The corresponding altitude, angle of attack, and equivalence ratio are 35-23km, 0°, and 0.426 respectively. H2 and OH mass fraction show that the upstream recirculation region generated by the fuel injection has flame-holding effects. Two-dimensional simulation reasonably predicts combustor inner pressure distribution and reveals periodic combustion characteristics of HyShot scramjet combustor. Altitude effects are also investigated and the strength of instability and subsonic boundary layer thickness affect the combustion efficiency according to altitudes.

Original languageEnglish
Title of host publicationA Collection of Technical Papers - 14th AIAA/AHI International Space Planes and Hypersonics Systems Technologies Conference
Pages1305-1315
Number of pages11
Publication statusPublished - 2006
Event14th AIAA/AHI International Space Planes and Hypersonics Systems Technologies Conference - Canberra, Australia
Duration: 2006 Nov 62006 Nov 9

Publication series

NameA Collection of Technical Papers - 14th AIAA/AHI International Space Planes and Hypersonic Systems and Technologies Conference
Volume2

Conference

Conference14th AIAA/AHI International Space Planes and Hypersonics Systems Technologies Conference
CountryAustralia
CityCanberra
Period06-11-0606-11-09

All Science Journal Classification (ASJC) codes

  • Engineering(all)

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