基于等离子流动控制的翼型减阻技术  

Airfoil drag reduction technique based on plasma flow control

作　　者：王元元[1] 周铸 陈明环 WANG Yuanyuan;ZHOU Zhu;CHEN Minghuan(Institute of Science and Technology Strategy and Systems Engineering, Aviation Industry Development Research Center of China, Beijing 100012, China;Overall Technology Department, China Aerodynamics Research and Development Center, Mianyang 621000, Sichuan, China)

机构地区：[1]中国航空工业发展研究中心科技战略与系统工程研究所,北京100012 [2]中国空气动力学研究与发展中心总体技术部,四川绵阳621000

出　　处：《计算机辅助工程》2021年第3期67-72,共6页Computer Aided Engineering

摘　　要：为研究基于等离子流动控制的减阻技术,基于Langtry-Menter转捩模型提出边界层转捩数值模拟技术。该技术可有效结合转捩模型与湍流模型,用标准模型验证其精确性,为采用等离子流动控制抑制边界层分离和转捩研究提供数值模拟平台。采用基于现象学模型的等离子流动控制数值模拟技术,对流动分离以及边界层转捩抑制进行数值模拟,为基于等离子流动控制的翼型减阻技术提供参考。To study the drag reduction technology based on plasma flow control,the numerical simulation technology of boundary layer transition is proposed based on Langtry-Menter transition model.The technique can effectively combine the transition model and turbulence model,and its accuracy is verified by standard model.It provides a numerical simulation platform for the suppression of boundary layer separation and transition by plasma flow control.The numerical simulation technology of plasma flow control based on phenomenological model is adopted to numerically simulate the flow separation and boundary layer transition suppression.It provides a reference for airfoil drag reduction technology based on plasma flow control.

关 键 词：等离子流动控制 流动分离 边界层 转捩 现象学模型 

分 类 号：TP391.99[自动化与计算机技术—计算机应用技术] V211.412[自动化与计算机技术—计算机科学与技术]