物面摩擦阻力是未来空天飞行器总阻力的关键组成部分，减小湍流条件下的摩擦阻力对于提高飞行器气动性能、节约能源具有重要意义。近年来，基于表面电弧放电等离子体激励器因其结构简单、激励频带宽、响应速度快等优点，在高速边界层的主动控制方面已取得系列探索性进展，但是对于最基础的等离子体气动激励与超声速湍流边界层相互作用这一基础问题仍缺乏详细定量的研究。本文针对以上问题，通过采用唯象模型模拟等离子体气动激励，并直接求解Navier-Stokes方程研究了频率为50 kHz的脉冲激励对Ma=2.9超声速湍流边界层流动结构、湍流统计量及壁面物理量的影响。结果表明，等离子体激励使得下游边界层内平均温度升高，平均密度降低，平均流向速度出现拐点，导致边界层外层出现Kelvin-Helmholtz剪切不稳定现象；对边界层内的雷诺应力和湍动能整体上均呈现减弱趋势；此外，激励对下游具有一定减阻效果，最大减阻率约为28.4%，主要原因在于湍动能生成的减小和分子粘性耗散作用的降低，而激励附近出现局部增阻，主要原因为诱导冲击波在边界层内产生的逆压梯度。

Skin friction drag is a critical component of total drag for future aerospace vehicles. Reducing the skin friction drag under turbulent flow conditions is of great significance for improving the aerodynamic performance and saving energy of the vehicles. In recent years, active flow control techniques utilizing surface arc discharge plasma actuators have achieved a series of exploratory advancements in the control of high-speed boundary layers due to their simple struc-ture, broad frequency bandwidth, and rapid response characteristics. However, detailed quantitative research on the interaction between the plasma excitation and supersonic turbulent boundary layer, which is an essential fundamental problem, remains limited. This study addresses this gap by directly solving the Navier-Stokes equations with a plasma phenomenological model. The effects on flow structures, turbulence statistics, and wall quantities of a Mach 2.9 su-personic turbulent boundary layer actuated by a plasma at a frequency fp=50 kHz were elucidated. The results indi-cate that the plasma actuation leads to an increase in mean temperature and a decrease in mean density within the boundary layer, with an inflection point appearing in the mean streamwise velocity profile. This triggers Kelvin-Helmholtz shear instability in the outer layer of the boundary layer. Furthermore, Reynolds stresses and turbulent ki-netic energy exhibit an overall reduction trend across the boundary layer in the downstream of the plasma location. Notably, the actuation achieves a maximum drag reduction rate of approximately 28.4% in the downstream region, which mainly ascribed to the decrease in the production of turbulent kinetic energy and molecular viscous dissipation. Conversely, drag enhancement occurs very close behind the actuation, which is a result of adverse pressure gradients generated by precursor blast waves within the boundary layer.