纳秒脉冲表面介质阻挡等离子体激励唯象学仿真?

赵光银; 李应红; 梁华; 化为卓; 韩孟虎

doi:10.7498/aps.64.015101

空军工程大学航空航天工程学院，等离子体动力学重点实验室，西安 710038

Phenomenological mo deling of nanosecond pulsed surface dielectric barrier discharge plasma actuation for flow control

摘要: 结合NS-DBD实验数据和理论分析，建立NS-DBD单区非均匀唯象学模型，旨在通过合理的模型进行流动控制仿真，揭示流动控制机理.在平板无来流时，运用单区非均匀唯象学模型，通过引入涡量输运方程，求解涡量方程各项，分析展向涡形成机理.展向涡主要是由压力升诱导激励区压力梯度和密度梯度的不正交性产生的，其次是激励区附近流场的对流引起的涡量转移.圆柱上的激励仿真得到与实验一致的压缩波结构和冲击波位置，验证了模型合理性. NACA 0015翼型大迎角分离控制的仿真表明，激励诱导展向涡促使主流和分离流相互作用，使分离点移向下游；脉冲激励频率通过诱导展向涡的数量对流动分离产生不同的作用效果，本文最佳的无量纲激励频率为6.

关键词:

Abstract: One-zone inhomogeneous phenomenological nanosecond dielectric barrier discharge (NS-DBD) actuation model used for flow control simulation is established to investigate the flow control mechanisms, based on experiments and theoretical analysis. When the inhomogeneous phenomenological model is applied to a plate, the formation of spanwise vorticity is analyzed through the vorticity transport equation, and the spanwise vorticity is mainly engendered due to the baroclinicity of pressure gradient and density gradient, also due to the vorticity transfer by the flow convection in the vicinity of the actuation region. Agreement of the simulation with experiments on a column shows that the inhomogeneous phenomenological NS-DBD actuation model is reasonable. Separation control over NACA 0015 airfoil at high angle of attack indicates that the spanwise vortices induced by plasma actuation make the separated shear layer instable, promote interaction between shear layers, and downstream the separation point. Different excitation frequency has different effect on the lift, with the optimum reduced frequency F+≈6 in current simulation.

纳秒脉冲表面介质阻挡等离子体激励唯象学仿真?

空军工程大学航空航天工程学院，等离子体动力学重点实验室，西安 710038

关键词:

Phenomenological mo deling of nanosecond pulsed surface dielectric barrier discharge plasma actuation for flow control

空军工程大学航空航天工程学院，等离子体动力学重点实验室，西安 710038

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