二元超声速进气道扩张段内伪激波特性  

Pseudo-shock characteristics in the two-dimensional supersonic inlet diffuser

作　　者：马广甫 谢文忠 林宇 靖建朋[2] 

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016 [2]中国人民解放军驻西安飞机工业(集团)有限责任公司军事代表室,西安710089

出　　处：《航空动力学报》2017年第8期1950-1961,共12页Journal of Aerospace Power

摘　　要：针对一种二元超声速进气道扩张段内伪激波特性,采用数值仿真方法对扩张段长度、扩张比和中心线偏距等参数的影响规律进行了研究。结果表明:在研究范围内,扩张段长度与扩张比对扩张段内伪激波特性影响较大,中心线偏距影响较小;扩张段长度与扩张比均会影响激波串长度及分离区的大小,从而对伪激波性能产生影响;基于一系列扩张段型面的仿真数据,给出了一个最大扩压性能对应的最佳扩张比的简单线性拟合公式。上述研究结果对超声速进气道扩张段设计具有参考价值。For pseudo-shock characteristics in the two-dimensional supersonic inlet diffuser,the influences of the diffuser length,diffusing ratio and the center line offset were numerically studied.Results show that：within the scope of the study,the influences of the diffuser length and diffusing ratio on the pseudo-shock characteristics are more significant than the center line offset.Both the diffuser length and diffusing ratio affect the pseudoshock characteristics by changing the shock train length and the scale of separation.Based on the numerical results of a series of diffuser geometries,a simple linear fitting formula to estimate the optimum diffusing ratio corresponding to the maximum diffusion performance has been proposed.These results are beneficial to the design of the supersonic inlet diffuser.

关 键 词：超声速进气道 扩张段 伪激波 扩张段长度 扩张比 中心线偏距 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]