Turbulent hypervelocity fuel/air mixing by cantilevered ramp injectors

B. Parent, J. P. Sislian

Research output: Contribution to conferencePaperpeer-review

9 Scopus citations

Abstract

An injector geometry is considered for fuel delivery in a high enthalpy, high Mach number airflow typical of that found in hypersonic propulsion systems such as the scramjet and shock-induced combustion ramjet or shcramjet. It is thought to embody the characteristics of both conventional ramp and low-angle wall injection techniques. The objective of the present paper is to investigate the turbulent hypervelocity fuel/air mixing characteristics of the considered injector geometry, with particular emphasis on the effect of the convective Mach number on its mixing efficiency. The analysis of the three-dimensional hypervelocity mixing flow is based on the Favre-averaged Navier-Stokes equations for a multi-species gas closed by the kw turbulence model. A Roe scheme turned second order through a symmetric TVD limiter is used for the spatial discretization while approximate factorization is used to iterate in pseudo-time. Obtained results show that the mixing efficiency varies by 31% for a convective Mach number ranging from 0 to 1.5 while the associated mass averaged stagnation pressure varies by only 10%.

Original languageEnglish (US)
DOIs
StatePublished - 2001
Externally publishedYes
Event10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference 2001 - Kyoto, Japan
Duration: Apr 24 2001Apr 27 2001

Conference

Conference10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference 2001
Country/TerritoryJapan
CityKyoto
Period4/24/014/27/01

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering
  • Control and Systems Engineering

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