面向高机动飞机起降增升实际工程问题，针对某大后掠薄三角翼大舵偏构型，基于主动流动控制射流环量增升机理，结合数值模拟和风洞试验两种设计及验证方法，实现了高机动飞机大后掠机翼流动控制增升的目标。大舵偏下机翼内侧襟翼与外侧副翼均存在流动分离，通过设置不同位置、不同角度的射流控制，考虑引气压比和引气流量的工程限制，实现了控制效果最佳、工程可行性最高的机翼外侧添加射流方案。考虑飞机主动流动控制状态参数复杂，对射流增升控制效果进行相似准则研究，发现不同工况下可用动量系数统一衡量射流控制效果。最后通过风洞试验校核，解释相关流动机理，最终形成了一套标准化理论研究方法及工程可行性高的高机动飞机环量控制机翼增升方案。
Addressing practical engineering problems related to lift augmentation during takeoff and landing to highly maneuverable aircraft, this study focuses on a thin large-sweep delta-wing with large rudder deflection. Based on the jet circulation control mechanism of active flow control, and combining both numerical simulations and wind tunnel experiments for design and validation, the goal of lift augmentation via flow control for wings of large-sweep highly maneuverable aircraft has been achieved. Flow separation occurs on both the inner flap and the outer aileron under large rudder deflection. By implementing jet control at different positions and angles, and considering engineering constraints such as bleed pressure ratio and bleed flow rate, the most optimal and feasible outer-wing jet scheme was realized. Considering the complexity of parameters about active flow control, a similarity criterion study was conducted on jet control, revealing that the control effect can be uniformly evaluated using the momentum coefficient under different conditions. Finally, wind tunnel tests were conducted to verify the results and elucidate the relevant flow mechanisms, ultimately establishing a standardized theoretical research method and a highly feasible circulation control wing lift augmentation scheme.
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