摘要
机翼采用的吹气襟翼偏度很大,由于在前缘产生强大的吸力峰值,会导致失速迎角明显减小。这个问题可以采用可移动的前缘装置来解决,这些装置改善了压力分布,增加了失速迎角,并提高最大升力系数。通常情况下,前缘装置需要在整个前缘布置,但是由于螺旋桨飞机的特殊性,仅在没有滑流影响的外翼段布置即可达到延迟失速的效果。首先针对机翼外翼进行前缘缝翼的二维剖面优化设计,分析了前缘缝翼对翼型失速迎角的影响,然后在三维方案上进行了仿真分析,计算模型考虑了螺旋桨滑流和襟翼吹气的影响,并进行了风洞试验验证。结果表明,采用吹气襟翼的机翼外侧设计前缘缝翼以后,在有动力条件下,失速迎角提高5°,最大升力系数增加0.3。
Due to the large deflection of the blowing flap,the stall angle of attack is reduced obviously because of the strong peak suction at the leading edge.This problem can be solved by using movable leading edge devices which improve the pressure distribution,increase the stall angle of attack and increase the maximum lift coefficient.Usually,the leading edge device needs to be placed over the entire leading edge,but because of the special nature of the propeller,the stall can be delayed only at the outer airfoils where there is no slipstream effect.Firstly,the leading-edge slats of two-dimensional profiles are optimized for the outer wing,and the effect of the leading-edge slats on the stall angle of attack is analyzed,then the three-dimensional module is simulated and analyzed,the computational model takes into account the effects of propeller slipstream and flap blowing,and is verified by wind tunnel tests.The results show that the stall angle of attack increases by 5°under dynamic conditions when the leading-edge slats are added to the outer wing of the airfoil with blowing flaps,and the maximum lift factor increases by 0.3.
作者
温庆
程志航
邱亚松
杨康智
Wen Qing;Cheng Zhihang;Qiu Yasong;Yang Kangzhi(China Aviation Industry General Aircraft Institute Co.,Ltd.,Zhuhai 519040,China;College of Aeronautics,Northwestern Polytechnical University,Xi’an 710071,China)
出处
《气动研究与试验》
2023年第3期88-96,共9页
Aerodynamic Research & Experiment
关键词
吹气襟翼
前缘缝翼
失速迎角
螺旋桨滑流
blowing flap
leading-edge slat
stall angle of attack
propeller slipstream
