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Boundary-layer receptivity and breakdown in hypersonic flow over a swept blunt wedge with three-dimensional freestream acoustic disturbances

机译:具有三维自由流声扰动的扫平钝楔上高超声速流动的边界层接受性和破坏

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Leading-edge receptivity and breakdown mechanisms of a hypersonic boundary layer in a Mach 6 flow over a blunt wedge of 4° half-wedge angle are investigated through direct numerical simulations (DNS) of the Navier-Stokes equations, with three-dimensional freestream fast and slow acoustic waves, in both an unswept and a swept configuration, and for two different Reynolds numbers. It is known that acoustic noise is a major contributor to freestream disturbances in hypersonic wind tunnels, and that the receptivity mechanism is strongly coupled to both the strength of the sound pressure level and the orientation of the acoustic disturbances. For this reason, the three-dimensional wave system consists of a main two-dimensional wave and two opposite angle oblique waves of lower amplitude, with multiple frequencies and spanwise wavenumbers. Moreover, the simulations are performed for two different levels of the freestream disturbance amplitude. The results show that fast acoustic waves with a high amplitude level are more efficient than slow waves in generating streaks in the nose region. These streaks grow downstream and lead to breakdown, in both the unswept and swept configurations. This appears to be related to the strong resonance mechanism at the leading edge characterising the receptivity to fast acoustic waves. Slow acoustic waves, in contrast, produce in the early nose region a wall response of lower amplitude, characterised by a more complex three-dimensional wave structure, which does not trigger transition in the unswept case even at the high amplitude level. In contrast, in the infinite swept case, both slow and fast acoustic waves lead to breakdown at both amplitude levels, with the higher amplitude leading to complete transition. Two different breakdown mechanisms are identified for the swept configuration, one for fast acoustic waves at the high amplitude level, which appears to be stronger as it leads to transition at an earlier position, through the generation and rapid growth of high-wavelength streamwise streaks, and another for all the other wave-type/amplitude combinations, which is triggered further downstream through the development of smaller-scale streamwise-oriented streaks.
机译:通过Navier-Stokes方程的直接数值模拟(DNS),利用三维自由流快速运动,研究了在4°半楔形角的钝楔上的Mach 6流中高超声速边界层的前沿接受性和破坏机理。和慢声波,无论是未扫频的还是扫频的,以及两个不同的雷诺数。众所周知,声噪声是高超声速风洞中自由流扰动的主要因素,并且接收机制与声压级的强度和声扰动的方向密切相关。因此,三维波系统由一个主二维波和两个振幅较小,频率和展向波数较小的对角斜波组成。此外,针对两个不同水平的自由流干扰幅度执行了仿真。结果表明,在鼻部区域产生条纹时,具有高振幅水平的快速声波比慢速波更有效。这些条纹在未扫掠和扫掠构造中都向下游生长并导致击穿。这似乎与前沿的强共振机制有关,表征了对快速声波的接收能力。相反,缓慢的声波在鼻子的早期区域产生较低振幅的壁响应,其特征在于更复杂的三维波结构,即使在高振幅水平下,它也不会触发未扫描情况下的跃迁。相反,在无限扫频的情况下,慢声波和快声波都会导致两个振幅水平的击穿,而更高的振幅会导致完全过渡。对于扫掠配置,确定了两种不同的击穿机制,一种是针对高振幅水平的快速声波,由于通过高波长流状条纹的产生和快速增长,它导致在较早位置发生过渡,因此似乎更强,对于所有其他波浪类型/振幅组合,则是另一种,这是通过开发较小规模的,沿流向的条纹进一步向下游触发的。

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