关键词: 高亚音速, 纳秒脉冲, 冲击波, 流动结构, 流动分离, 影响规律

Abstract: In order to research the mechanism of nanosecond pulsed plasma aerodynamic actuation flow control on the high subsonic speed compressor cascade, the heat source model based on the phenomenology is established to simulate the nature of nanosecond pulsed dielectric barrier discharge. The influence law of nanosecond pulsed plasma aerodynamic actuation on compressor cascade flow field is researched in detail from a microsecond time scale perspective, and the preliminary research on the nanosecond pulsed plasma aerodynamic actuation flow control is delivered. Results are: the heat source model based on the phenomenology is successful in modeling the aerodynamic performance of the shock wave produced by nanosecond pulsed plasma aerodynamic actuation; under the condition of high subsonic speed, the shock wave produced by the nanosecond pulsed plasma aerodynamic actuation still has a dramatic impact on the structure of compressor cascade flow field, and the impact is influenced by the actuation feature and the character of the flow field; although the inlet flow is high subsonic, the nanosecond pulsed plasma aerodynamic actuation is capable of decreasing the total pressure loss at the outlet of the compressor cascade passage, and changing the structure of the flow field.

Key words: high subsonic, nanosecond pulse, shock wave, flow structure, separation structure, influence law