翼型外形与激励参数对等离子体流动控制的影响

Influence of Airfoil Profile and Excitation Parameters on Plasma Flow Control

流动控制能够改善翼型受力状态从而提高气动特性,等离子体流动控制作为一种主动流动控制技术是当前研究的热点之一。本文采用等离子体唯象学模型,该模型忽略等离子体激励对动量的影响只考虑能量的注入对热效应的影响,将其与流动N-S方程相耦合方法,使用数值模拟手段研究等离子体气动激励对不同几何外形的翼型流动分离控制效果。模拟结果表明:施加等离子体激励可以增升减阻提升翼型气动特性,同时对翼型流动分离有控制作用,随翼型厚度增加使C_(l)增加量从147.7%下降到72.6%,弯度增加使C_(l)增加量从147.7%下降到19.6%,激励流动控制效果减弱且最大厚度位置靠前或靠后均削弱激励控制效果。此外流动控制作用与激励参数有关,改变激励电压峰值和频率都会对控制效果产生影响。通过研究分析可以为后续的翼型选型和更好的选择激励参数提供帮助。

Flow control can improve the force state of airfoil and thus improve the aerodynamic characteristics.As an active flow control technology,plasma flow control is one of the hot spots in current research.In this paper,a plasma phenomenological model is adopted,which ignores the influence of plasma excitation on momentum and only considers the influence of energy injection on heat effect.The model is coupled with the flow N-S equation to study the control effect of plasma aerodynamic excitation on airfoil flow separation with different geometric shapes by numerical simulation.The simulation results show that:The application of plasma excitation can improve the aerodynamic characteristics of airfoil by increasing lift and drag,and control the flow separation of airfoil.With the increase of airfoil thickness,the increase of C_(l)decreases from 147.7%to 72.6%,and the increase of C_(l)decreases from 147.7%to 19.6%with the increase of bend.The control effect of the excitation flow is weakened and the position of the maximum thickness is near the front or back.In addition,the flow control function is related to the excitation parameters,and changing the excitation voltage peak and frequency will affect the control effect.The research and analysis can provide help for subsequent airfoil selection and better selection of excitation parameters.