关键词: 超燃冲压发动机;超声速燃烧;燃烧化学动力学;氢;反应流;数值仿真

Abstract: The flow of H 2/Air mixture ignited by a blund body shock was simulated numerically with an uncoupled non equilibrium method, based on N S equations and ENO scheme. The application of method was simple in structure and efficient for modifying to multi component and multi reaction chemical mechanism. The comparisons of superdetonative and transdetonative speeds were made with 7 species and 8 reactions chemical mechanism introduced by Evans and Schexnayder, 9 species and 19 reactions chemical mechanism and 13 species and 32 reactions chemical mechanism introduced by Jachimowski. The second chemical mechanism without reactions about N atom was suitable to simulate H 2/Air combustion which flight Mach number was below 7.

Key words: Supersonic combustion ramjet engine;Supersonic combustion;Combustion chemical kenetics;Hydrogen;Reacting flow;Numerical simulation