摘要
尾喷流是飞行器主要的红外辐射源之一,采用微喷射流技术能够对尾喷流红外辐射进行有效控制.对将微喷射流技术用于尾喷流混合进行数值模拟,研究结果表明:采用微喷射流技术后,在尾喷流中形成流向涡,强化了尾喷流与周围空气的掺混,高温核心区面积减小,并且发现微喷射流的出口横向尺寸和微喷射流在主喷流中的穿透深度是影响掺混的决定性因素.
Computational fluid dynamics is employed to numerically simulate the flow of round jet with microjet. With microjet technology, it＇s possible to control efficiently IR of jet flow. And, vortexes in flow direction are generated to enhance the mixing between jet flow and ambient air. Therefore the high temperature area of jet is decreased. The penetration and outlet width of microjet is the decisive factor to suppress the high temperature area and affect the mixing.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第11期1966-1970,共5页
Journal of Aerospace Power
关键词
微喷射流
喷流混合
温度分布
aerospace propulsion system
microjet
jet mixing
temperature distribution
