中文摘要：

针对低速条件下等离子体气动激励抑制压气机叶栅吸力面流动分离进行研究。将表面介质阻挡放电等离子体气动激励对流场的作用等效为体积力和热的作用，并考虑等离子体温升对流体热物理性质的影响，建立了等离子体气动激励的数学模型。通过求解电势和电荷方程得到等离子体气动激励诱导的体积力和热功率密度分布函数，通过实验数据拟合得到物性参数函数，分别作为方程源项和系数加入到Navier—Stokes方程中求解。应用模型研究了等离子体激励在不同来流速度、攻角和激励强度下对压气机叶栅性能的影响。数值仿真结果表明：在马赫数为0．05、攻角为2。的情况下，施加等离子体激励后，分离点由65．09％弦长处后移到79．4％弦长，气流转折角增加0．8，最大总压损失系数减小了7．4％，尾迹宽度减小了12％。来流速度增大激励效果会减弱，来流攻角的改变对激励效果有影响，激励强度增大对流动分离的抑制效果有明显改善。

英文摘要：

The mathematical model of plasma flow control is established by regarding the influences of the plasma aerodynamic actuation on the fluid as body force and thermal energy and considering the influences of the plasma temperature rise on the thermal physical property of fluid. The body force and thermal ener- gy profile function obtained by solving the potential equation and the charge equation and the thermal phys- ical property function obtained by fitting experimental data are added to the Navier-Stokes equation as source terms and coefficient respectively. Simulation investigation of flow separation control on a compres- sor cascade by plasma aerodynamic actuation is performed under low velocity conditions. The influence of the flow velocity, incidence and the intensity of plasma aerodynamic actuation on the performance of com- pressor cascade is investigated. After actuation in the case of Ma = 0.05 at an incidence of 2~, the location of separation point is moved from 65.09 % to 79.4% of the chord, the flow turning angle is increased about 1, the maximum total pressure loss coefficient is reduced about 7.4% and the width of the trail is reduced about 12%. The actuation effect is reduced with the increase of air flow velocity. The change of incidence affects the actuation effect. The actuation effect is obviously improved with the increase of the intensity of plasma aerodynamic actuation.