等离子体气动激励抑制翼型失速分离的仿真研究

梁华; 李应红; 程邦勤; 马清源; 武卫

等离子体气动激励抑制翼型失速分离的仿真研究

空军工程大学工程学院, 西安 710038

基金项目: 国家“863”计划(2005AA753031);空军工程大学工程学院优秀博士论文创新基金(BC07001)

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出版历程
- 收稿日期: 2007-11-29
- 修回日期: 2008-03-01
- 刊出日期: 2008-05-28

Numerical simulation on airfoil stall separation suppression by plasma aerodynamic actuation

The Engineering Institute, Air Force Engineering University, Xi′an 710038, China

摘要

摘要: 通过求解表面放电的二维流体体力模型,建立了翼型等离子体流动控制的数学模型,得到等离子体气动激励诱导的体力和热量分布,与Navier-Stokes方程耦合求解.进行了低雷诺数条件下,等离子体气动激励抑制NACA0009翼型失速分离的数值仿真研究,研究了等离子体激励的强度、激励电极数目和激励位置对流动分离抑制和翼型升阻特性的影响.在雷诺数为58000、攻角为24°的情况下,施加等离子体激励后,升力系数由0.7449增大到1.2404;阻力系数由0.4012减小到0.3503.
- 航空、航天推进系统 /
- 介质阻挡放电 /
- 等离子体气动激励 /
- 流动控制 /
- 翼型 /
- 失速分离
Abstract: The mathematical model of plasma flow control on airfoil was established by solving a two-dimensional fluid model of surface discharge.The body force induced by the plasma aerodynamic actuation was obtained.The momentum and thermal energy were added to the Navier-Stokes equation as source terms.Simulation investigation of plasma flow control on NACA0009 airfoil stall separation suppression was performed under low Reynolds number conditions.The influence of the intensity of the plasma aerodynamic actuation as well as the electrode number and position was investigated.The lift coefficient increased from 0.7449 to 1.2404 and the drag coefficient reduced from 0.4012 to 0.3503 after actuation in the case of Re=58000 at an angle of attack of 24°.
- aerospace propulsion system /
- dielectric barrier discharge(DBD) /
- plasma aerodynamic actuation /
- flow control /
- airfoil /
- stall separation

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参考文献(13)

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