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This paper numerically studies the dynamics of Symmetrical-wedge shock intersection under sinusoidal supersonic oscillation conditions. The 15◦ symmetrical wedges are used as the shock generator, the sinusoidal oscillation is used as the inflow condition. Two forms are considered:(I)The fluctuation amplitude is kept constant(A=1.4), the influence of the fluctuation frequency from 4kHz with a step of 2kHz to 10kHz on the shock wave system is considered. (II) Keeping the frequency constant (f=10kHz), the effect of three amplitudes (A=1.0,1.4,1.8) on shock waves is considered. A detailed analysis of unsteady flow features, including the Mach stem growth, the swing of slip lines, pressure evolution, peculiar pressure wave phenomenon are presented with a focus on the bi-directional regular intersection (RI↔MI) Mach intersection transition process. The study found that:RI↔MI always occurs near the von Neumann solution, there are premature transformations and hysteresis. The higher the frequency, the more obvious the hysteresis and premature transformation are, the more obvious the swing of slip lines is. The lower the frequency, the longer the bi-directional transition time of the RI↔MI, the greater the maximum height of the Mach stem, the more frequent the triple points' pressure fluctuation. In addition, the oscillating flow will cause the propagation of pressure waves in the slip line channel and the transition from transverse waves to longitudinal waves. Under the different amplitudes, the greater the amplitude is, the greater the height of the Mach stem is. When the amplitude is maximum, the evolution of the detached shock wave will lead to the complexity of the system.

In this paper, delayed detached eddy simulations are performed to study wake flows of a turbine blade at a high subsonic exit Mach number, M 2,is ¼ 0:79, and high Reynolds number, Re ¼ 2:7 À 2:8 Â 10 6 , based on the chord length and outlet velocity. It is found that a slight change in the trailing suction profile would have a big influence on the formation of wake vortex street, which is believed to be caused by the change in the boundary layer state near the trailing edge, and suction boundary layer with a fuller velocity profile tends to destabilize the wake flow, promoting the generation of wake vortex and enhancing the unsteady effect. Local spatial-temporal stability analyses of the wake velocity profiles suggest that wake flows with asymmetric velocity profiles might have a stabilizing effect. It is suggested that the vortex formation and its strength can be controlled by making some slight modifications on the rear blade suction surface, and the mixing loss in the wake can be reduced due to a weaker unsteady effect.

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