大型飞机襟翼吹气增升风洞试验

doi:10.7527/S1000-6893.2022.27870

Abstract

Abstract:

The lift of large aircraft can be effectively enhanced with the technology of flap blowing， attracting extensive research and attention in recent years. To improve the take-off and landing performance of a certain type of aircraft， we conduct the flap blowing test in the FL-14 wind tunnel. The two-channel mass flow control unit is used to measure and control the flow of the inboard and outboard flap， and the external air bridge is adopted to eliminate the influence of the air supply pipeline on the force balance measurement. The effect of pressure， temperature and flow rate on the balance load and that of momentum coefficient and flap deflection angle on the lift are studied through the air bridge test and the wind tunnel test， respectively. The surface flow field is visualized with fluorescent tufts. The test results show that the lift increases significantly with flap blowing， and the increment of the lift coefficient increases with the moment coefficient， with the maximum increment being 1.15. The stall angle of attack increases slightly with the momentum coefficient at the flap deflection angle of 30°/ 22.5°. Larger flap deflection angles firstly increase the stall angle of attack and then decrease and finally increase with the increasing momentum coefficient. Lift increment is proportional to the natural logarithm of the momentum coefficient， while both the slope and intercept of the fitting curve increase with the growing flap deflection angle.

Key words: flap blowing, flow control, lift enhancement, wind tunnel test, large aircraft

CLC Number:

V211.4

Wanbo WANG, Yubiao JIANG, Yong HUANG, Xin ZHANG, Ran WEI. Lift enhancement wind tunnel test with flap blowing for large aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(13): 0.

Figures/Tables 17

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指标	载荷/N			力矩/（N·m）
指标	F_y	F_x	F_z	M_y	M_x	M_z
设计值	10 000	3 300	13 000	3 000	14 000	6 000
校准值	10 000	3 750	13 000	3 240	13 500	6 000
精确度/%	0.05	0.05	0.05	0.05	0.05	0.05
准确度/%	0.20	0.23	0.10	0.24	0.10	0.10

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Lift enhancement wind tunnel test with flap blowing for large aircraft

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