中文摘要：

开展了微射流控制参数对飞翼布局无人机（UAV）气动特性影响规律的研究.建立的流动控制模型及数值模拟技术经过了TAU0015翼型流动控制试验校核.设计了布置于飞行器前缘和1％c处的8套阵列式微射流控制方案,研究了微射流技术的气动控制效果,分析了典型流动控制参数对控制效能的影响规律.研究结果表明：微射流技术可以有效改善飞翼布局UAV大迎角下的流动分离现象,升力系数增幅达25％,布置于飞行器前缘和内翼段的射流激励器控制效果较优,较大的射流动量系数对流场影响较大,最优的无量纲射流频率为1.

英文摘要：

The control effectiveness of typical micro-jet flow control parameters on the aerodynamic performance of the flying-wing unmanned aerial vehicle （UAV） is investigated by numerical simulation.Validation is conducted with TAU0015 airfoil experimental data for flow control model and numerical method.The flow control model is tested with eight arrays of synthetic jet actuators embedded in the leading edge and 1％ c along the wing span.The change in the control effect is examined and the control efficiency of control parameters is performed.The numerical results of the UAV aerodynamic coefficients reveal lift coefficient increments over the baseline uncontrolled case as large as 25％.The actuators arranged in leading edge and inboard of UAV are found to be more effective at separation control,the larger jet momentum coefficient are more pronounced and the most effective jet frequency seemed to be one,which indicate that correct control parameter is critical to the design of an efficient flow separation control scheme.