高机动飞机主动流动控制环量增升设计

doi:10.7527/S1000-6893.2026.33440

Abstract

Abstract:

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.

Key words: circulation control, Coanda effect, lift augmentation, similarity criteria, wind tunnel test

CLC Number:

V211.41

Jiawei FU, Chen WANG, Min’ang MA, Hong WANG, Tong ZHAO, Jintong LIU. Design of lift augmentation via circulation of active flow control to highly maneuverable aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(13): 533440.

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参数	前缘襟翼	后缘内侧襟翼	后缘外侧襟翼	副翼
展向位置/m	1.0~7.0	0~2.4	2.4~4.8	4.8~7.7
流向长度/m	0.3	1.7~2.0	1.3~1.7	1.0~1.3
偏转角度/（°）	-20	45	45	24

网格点数/10⁴	0°迎角		11°迎角
网格点数/10⁴	升力系数C_L	阻力系数C_D	升力系数C_L	阻力系数C_D
900	0.508 0	0.062 5	1.250 3	0.221 7
1 800	0.507 4	0.063 2	1.252 4	0.222 1
3 600	0.507 2	0.063 2	1.251 3	0.222 0

参数	法向力	轴向力	横向力	滚转力矩	偏航力矩	俯仰力矩
设计载荷/N	±12 000	±1 500	±700
校核载荷/N	±10 000	±1 500	±650
设计力矩/（N·m）				±2 000	±2 500	±500
校核力矩/（N·m）				±2 000	±2 500	±500
综合加载重复性/%F.S.	0.02	0.03	0.02	0.04	0.01	0.04
综合加载误差/%F.S.	0.06	0.03	0.03	0.21	0.08	0.06
合成标准不确定度/%F.S.	0.12	0.11	0.11	0.23	0.13	0.12
扩展不确定度/%F.S.	0.24	0.22	0.21	0.47	0.26	0.24

Design of lift augmentation via circulation of active flow control to highly maneuverable aircraft

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