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为了研究进气道喉道非均匀流场对隔离段流动特性的影响,设计了能模拟隔离段入射激波和非对称附面层的直连试验装置,并进行了马赫数3.0,3.4和3.8的吹风试验,完成了壁面静压、纹影和NPLS测量,获得了有效的试验数据。结果显示,唇口角对隔离段直连台的起动和耐反压能力影响非常大,随着唇口角度的增加,隔离段的极限反压降低,降低幅度达到22%~32%。与均匀来流相比,激波串很难稳在隔离段入口附近,造成激波串极易被推出隔离段。激波串形态受隔离段入射激波和肩部附近附面层状态的影响较大。NPLS测量系统观察到隔离段内部流场精细结构,如下壁面附面层的转捩现象、激波串的马赫盘、分离和滑移线等。
In order to study the influence of inhomogeneous flow field in inlet throat on the flow characteristics of isolated section, a direct-coupled test device was designed to simulate the incident shock wave and asymmetric surface layer in isolated section. Mach number 3.0, 3.4 and 3.8 Of the hair blowing test, completed the wall static pressure, Wen Ying and NPLS measurements obtained valid test data. The results show that the lip angle has a great influence on the starting and anti-backpressure capability of the direct stage of the isolation section. As the lip angle increases, the ultimate backpressure of the isolation section decreases to 22% -32%. Compared with the uniform flow, shock wave string is difficult to stabilize near the entrance of the isolation section, resulting in shock wave easily pushed out of the isolation section. The shape of the shock wave train is greatly affected by the incident shock waves in the isolated section and the state of the surface layer near the shoulder. The NPLS measurement system observed the fine structure of the flow field inside the isolation section, such as the transition of the wall surface undercoat, the Mach disk of the shock train, the separation and slip lines, and so on.