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 tests 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. Based on the numerical simulation scheme, wind tunnel tests were conducted to verify the results and elucidate the relevant flow mechanisms, establishing a standardized theoretical research method and a highly feasible circulation control wing lift augmentation scheme.