飞翼布局飞行器有望依靠射流主动流动控制技术实现无舵面飞行以改善隐身特性，但鲜有针对中等展弦比（3<A<4.5）战术级飞翼的相关研究。本文为中等展弦比飞翼布局无人机设计环量控制激励器取代传统副翼，开展全机数值模拟和飞行试验研究，探究后缘环量控制射流的滚转控制能力。数值模拟使用压力入口边界并考虑射流动量贡献的气动力，实现对飞翼绕流和激励器内流耦合模拟和整机气动特性预测。数值模拟研究表明，射流的滚转控制能力随射流动量系数线性增长，且未产生显著的横航向或横纵向耦合力矩。飞行试验结果表明，环量控制激励器实现了平均滚转角速率25.5-26.7°/s,最大滚转角速率40.1°/s,最大滚转角83.9°的控制效果。

With jet active flow control technologies, the flying-wing aircraft are expected to achieve flapless flight which can improve the stealth characteristics. However, little research has been done on the tactical flying-wing platforms with medium aspect ratio. In this paper, a circulation control effector (CCE) is designed to replace the ailerons of a me-dium-aspect-ratio flying-wing UCAV. Numerical simulations and flight tests of the demonstrator are conducted to investigate the roll control effectiveness of the trailing-edge circulation control jet. In numerical simulations, the pressure inlet boundary is adopted, and the contribution of jet momentum is also considered in the aerodynamic force calculation. Then, the coupling simulation of the inner flow in CCE and the outer flow over flying-wing UCAV is realized, and the demonstrator’s aerodynamic characteristics are predicted. The simulation results show that with the increase of jet momentum coefficient, the roll control capability increases almost linearly, and there is no obvi-ous coupling yaw moment or pitch moment. The flight test results indicate that a remarkable roll control effective-ness is achieved by the CCE, with mean roll rate of 25.5-26.7°/s, maximum roll rate of 40.1°/s, and maximum roll angle of 83.9°.