采用的数值计算模型和方法适用于分析中心进气式固冲发动机反应流场。
Numerical calculation model and method are applicable to analyzing reacting flow field of the solid rocket ramjet with central air-inlet mode.
数值仿真模型中考虑了自燃推进剂雾化机理、高压分解燃烧和预混反应流湍流燃烧等。
The atomization mechanism of hypergolic rocket propellant and decomposition combustion at high pressure and turbulence burning of premixed reactant flow field are considered .
模拟结果给出了突扩燃烧室内湍流预混反应流的气体时均流场、组分浓度场与温度场的分布。
The calculated results cover the time averaged gas flow field, species mass fraction and temperature distributions for the premixed reacting flow in the sudden expansion combustor.
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