中文摘要：

在一条高速度的飞机串联风隧道进行的试验性的调查由使用表明那不稳定的流动控制合成(零集体流动) 旋涡生成器喷气能有效地改进空气动力学的表演和还原剂(或消除) 在轴的压缩机串联的流动分离。到来的流动的马赫数字直到 0.7，大多数测试用例在妈 = 0.3。发生是界面层与 70% 弦长度在被分开的 10 °。刺激频率，振幅，地点和沥青角度的角色被调查。初步的结果证明刺激振幅起一个很重要的作用，最佳的刺激地点只分离点是在上游的，并且最佳的沥青角度是 35 °。损失系数的最大的相对减小是 22.8% 。

英文摘要：

An experimental investigation conducted in a high-speed plane cascade wind tunnel demonstrates that unsteady flow control by using synthetic （zero mass flux） vortex generator jets can effectively improve the aerodynamic performances and reduce （or eliminate） flow separation in axial compressor cascade. The Mach number of the incoming flow is up to 0.7 and most tested cases are at Ma = 0.3. The incidence is 10° at which the boundary layer is separated from 70% of the chord length. The roles of excitation frequency, amplitude, location and pitch angle are investigated. Preliminary results show that the excitation amplitude plays a very important role, the optimal excitation location is just upstream of the separation point, and the optimal pitch angle is 35°. The maximum relative reduction of loss coefficient is 22.8%.