Investigation of hypersonic cone boundary layer stability regulation with plasma actuation

Abstract

In this paper, wind tunnel experiments are carried out under Mach 6 flow to study the stability regulation of a hypersonic sharp cone boundary layer with nanosecond pulsed plasma actuation. First, the typical characteristic structure of the rope-like structure is captured by the high-speed schlieren method. Then, combining the sensor results and theoretical analysis, the rope-like structure and the dominant instability wave resolved by the schlieren power spectrum density (PSD) method are determined to correspond to the second-mode wave. The characteristic unstable quasi-ordered structure of the boundary layer under actuation is then extracted, and the impact effect and modulation effect of this structure on the second-mode wave are analyzed. Finally, the mechanism by which actuation influences the boundary layer instability is studied using proper orthogonal decomposition (POD). The results show that actuation can enhance boundary layer pulsation and the coupling effect between the actuation and boundary layer can produce regular unstable quasi-ordered structures. The intrinsic mechanism works by impinging on and modulating the second-mode waves, and there are characteristic modes of the rope-like structure and the unstable structures distributed over the whole flow-direction range. This verifies the ability of plasma actuation to stimulate the instability of hypersonic cone boundary layers and provides technical support for the further development of transition control methods.

Experimental Study on Hypersonic Double-Wedge Induced Flow Based on Plasma Active Actuation Array

“…In addition, a wind tunnel experiment was carried out under the condition of Mach number 6 to study the stability adjustment of the hypersonic blade. The results verify the ability of plasma actuation to stimulate the instability of hypersonic cone boundary layers and provide technical support for the further development of transition control methods [19]. Kong et al conducted experiments on the control of double-wedge flow by 10 discharge actuators under hypersonic conditions and analyzed the interaction evolution process between plasma surface arc discharge and a flow field in detail [21].…”

“…In the three working conditions, the longest control time was only 90 µs, the energy deposited into the flow field was above 4.1 J, and the repetition frequency was only 1 Hz [16]. However, surface arc plasma actuation shows excellent control effects in supersonic shock wave control, shock wave/boundary layer interaction, and forced supersonic boundary layer transition [17][18][19][20]. Yang conducted controlling hypersonic boundary layer transition using a surface arc plasma actuation array.…”

“…The influence of three different actuation frequencies (8,34, and 55 kHz) was studied based on linear stability theory analysis, and a transition criterion under the control of plasma actuation was proposed. Finally, the corresponding control mechanism was summarized, and the transition control mechanization was refined [17]. In addition, Yang experimented on the stability of the hypersonic plate boundary layer by using a spanwise plasma actuation array.…”