论文部分内容阅读
为了研究射流涡发生器对激波边界层作用所诱导的流动分离控制机理及其流场特性,基于大涡模拟(Large eddy simulation)方法和高阶TCD/WENO混合格式,对来流马赫数Ma=2.5情况下,平板上射流涡发生器对激波与边界层相互作用所诱导流场进行了数值模拟。结果表明,射流涡发生器对激波边界层的流体分离有一定的抑制作用,与无控制情况相比,射流作用下进出口总压恢复系数由85.9%提高到94.6%。射流尾涡主要集中于一环状区域内,在该区域内,入射激波与马蹄涡、桶形激波上方的涡管以及剪切涡相互作用,导致整体尾流被激波往下压缩。同时在激波的压缩下,各涡之间相互缠绕、挤压合并,形成多个流向小涡结构,将边界层外的高速流体卷入边界层内,从而增加边界层底层能量,达到抑制流动分离的目的。
In order to study the control mechanism of flow separation induced by jet vortex generator and its flow field induced by the shock boundary layer, based on the large eddy simulation method and the high order TCD / WENO hybrid scheme, the Mach number Ma = 2.5, the on-plate jet vortex generator numerically simulates the flow field induced by the interaction between the shock wave and the boundary layer. The results show that the jet vortex generator has some restraining effect on the fluid separation in the shock boundary layer. Compared with the non-control case, the total pressure at the inlet and outlet of the jet increases from 85.9% to 94.6%. The jet wake vortex mainly concentrates in a ring-shaped region, where the incident shock waves interact with the horseshoe vortex, the vortex tube above the barrel shock and the shear vortex, resulting in the overall wake being compressed downwards by the shock wave. At the same time, under the compression of the shock wave, the vortices are intertwined and squeezed together to form a plurality of small vortex structures, and the high-speed fluid outside the boundary layer is involved in the boundary layer, thereby increasing the energy of the bottom layer of the boundary layer to suppress the flow The purpose of separation.