摘要
The vortex dynamics of flow over an airfoil controlled by a nanosecond pulse dielectric-barrierdischarge(NS-DBD) actuator is studied at a Reynolds number of 1×10^5 through wind tunnel experiments and numerical simulation. The numerical method is validated through comparison of the simulated and measured results regarding the effect of the discharge of an NS-DBD actuator placed on a flat plate. The simulated results show that vorticity is mainly induced by the baroclinic torque after plasma discharge, i.e. the term(1/p^2▽p×▽p) in the equation of vorticity evolution. Both experimental and simulated results demonstrate that after the discharge of the NS-DBD actuator a series of vortices are developed in the shear layer and pull the high-moment fluid down to the wall, enhancing the mixing of internal and external flows.
The vortex dynamics of flow over an airfoil controlled by a nanosecond pulse dielectric-barrierdischarge(NS-DBD) actuator is studied at a Reynolds number of 1?×?10~5 through wind tunnel experiments and numerical simulation. The numerical method is validated through comparison of the simulated and measured results regarding the effect of the discharge of an NS-DBD actuator placed on a flat plate. The simulated results show that vorticity is mainly induced by the baroclinic torque after plasma discharge, i.e. the term(■) in the equation of vorticity evolution. Both experimental and simulated results demonstrate that after the discharge of the NS-DBD actuator a series of vortices are developed in the shear layer and pull the high-moment fluid down to the wall, enhancing the mixing of internal and external flows.
作者
杜海
王磊
孔文杰
史志伟
程克明
李铮
Hai DU;LeiWANG;Wenjie KONG;Zhiwei SHI;Keming CHENG;Zheng LI(School of Energy and Power Engineering,Xihua University,Chengdu 610039,People's Republic of China;Key Laboratory of Fluid and Power Machinery,Ministry of Education,Xihua University,Chengdu 610039,People's Republic of China;College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,People's Republic of China)
基金
supported by National Natural Science Foundation of China (No. 51806181)
the Open Research Subject of the Key Laboratory (Research Base) of Fluid and Power Machinery (Xihua University), Ministry of Education (szjj2017-086)
the Key Scientific Research Fund of Xihua University (No. Z17111)
the financial support of the Sichuan Provincial Department of Education (No. 18ZA0458)
the Key Laboratory of Aeroengine Pneumatic and Thermal Defense Science and Technology (No. 6142702180101)
the ‘Young Scholars’ Program of Xihua University
