航空学报2025，Vol.46Issue(z1)：87-99,13.DOI:10.7527/S1000-6893.2025.32187
等离子体激励超声速湍流边界层直接数值模拟
Direct numerical simulation of supersonic turbulent boundary layer with plasma actuation
摘要
Abstract
Skin friction drag is a critical component of total drag for future aerospace vehicles.Reducing the skin fric-tion 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 structure,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 funda-mental 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 number 2.9 supersonic turbulent boundary layer actuated by a plasma at a frequency 50 kHz were elucidated.The re-sults indicate 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 turbu-lent kinetic energy exhibit an overall reduction trend across the boundary layer in the downstream of the plasma loca-tion.Notably,the actuation achieves a maximum drag reduction rate of approximately 28.4%in the downstream re-gion,which mainly ascribed to the decrease in the production of turbulent kinetic energy and molecular viscous dissi-pation.Conversely,drag enhancement is observed near the actuation,caused by adverse pressure gradients gener-ated by precursor blast waves within the boundary layer.关键词
湍流/边界层/等离子体激励/直接数值模拟/摩阻分解Key words
turbulence/boundary layer/plasma actuation/direct numerical simulation/skin friction decomposition分类
航空航天引用本文复制引用
LI Chen,SUN Dong,LIU Pengxin,GUO Qilong,YUAN Xianxu..等离子体激励超声速湍流边界层直接数值模拟[J].航空学报,2025,46(z1):87-99,13.基金项目
国家自然科学基金(12202475,12472241,92371115) （12202475,12472241,92371115）
四川省自然科学基金(2023NSFSC0053) National Natural Science Foundation of China(12202475,12472241,92371115) （2023NSFSC0053）
Natural Science Foundation of Sichuan Province(2023NSFSC0053) （2023NSFSC0053）
