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针对自行设计的超燃冲压发动机进气道/隔离段+燃烧室一体化模型,进行了燃烧室实际超声速来流条件下的冷态全流场试验研究与数值模拟,获得了模型在不同来流总压和燃烧室出口反压下的流场结构及沿程静压力分布。试验真实模拟了冷流条件下燃烧室实际的进口环境,结果表明:当燃烧室反压系数较低时,激波串在燃烧室扩张段附近形成;当燃烧室反压系数较高时,激波串在燃烧室进口处形成,并且由于凹槽的影响,激波串向燃烧室上壁面偏斜。
According to the self-designed scramjet / scramjet / combustor integrated model, the full flow field test and numerical simulation of the cold flow under the actual supersonic flow in the combustor were carried out. The structure of the flow field under the total pressure and the pressure at the exit of the combustion chamber and the pressure distribution along the path. The experiment real simulated the actual inlet environment of the combustion chamber under the condition of cold flow. The results show that when the pressure coefficient of the combustion chamber is low, the shock wave forms near the expansion of the combustion chamber. When the pressure coefficient of the combustion chamber is high, The wave train is formed at the combustion chamber inlet and the shock train is deflected toward the upper wall of the combustion chamber due to the influence of the groove.