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 .
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 .
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