摘要
The turbulent boundary layer control on NACA 0012 airfoil with Mach number ranging from 0.3 to 0.5 by a spanwise array of dielectric barrier discharge(DBD)plasma actuators by hot-film sensor technology is investigated.Due to temperature change mainly caused through heat produced along with plasma will lead to measurement error of shear stress measured by hot-film sensor,the correction method that takes account of the change measured by another sensor is used and works well.In order to achieve the value of shear stress change,we combine computational fluid dynamics computation with experiment to calibrate the hot-film sensor.To test the stability of the hot-film sensor,seven repeated measurements of shear stress at Ma=0.3 are conducted and show that confidence interval of hot-film sensor measurement is from−0.18 to 0.18 Pa and the root mean square is 0.11 Pa giving a relative error 0.5%over all Mach numbers in this experiment.The research on the turbulent boundary layer control with DBD plasma actuators demonstrates that the control makes shear stress increase by about 6%over the three Mach numbers,which is thought to be reliable through comparing it with the relative error 0.5%,and the value is hardly affected by burst frequency and excitation voltage.
作者
李跃强
高超
武斌
王玉帅
郑海波
薛明
王玉玲
Yueqiang LI;Chao GAO;Bin WU;Yushuai WANG;Haibo ZHENG;Ming XUE;Yuling WANG(School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,People's Republic of China)
基金
the European Commission through the Research and Innovation action DRAGY(Drag Reduction via Turbulent Boundary Layer Flow Control)
under Grant No.690623
the Ministry of Industry and Information Technology(MIIT)of the Chinese government
support received from National Natural Science Foundation of China(No.11572256).