机翼上表面吹气动力增升简化模型  

Simplified model of wing upper surface blowing dynamic lift enhancement

作　　者：赵国昌 邢仕廷 宋丽萍 叶小鸽 ZHAO Guo-chang;XING Shi-ting;SONG Li-ping;YE Xiao-ge(College of Airworthiness,CAUC,Tianjin 300300,China;Sino-European Institute of Aviation Engineering,CAUC,Tianjin 300300,China)

机构地区：[1]中国民航大学适航学院,天津300300 [2]中国民航大学中欧航空工程师学院,天津300300

出　　处：《飞行力学》2018年第4期39-43,共5页Flight Dynamics

基　　金：中国民航大学蓝天学者研究基金资助(20162020)

摘　　要：利用安装在机翼上表面的发动机喷出的尾部高速气流增加机翼升力是一种有效的动力增升技术。不考虑流动分离的影响,建立从发动机尾喷口到襟翼前和沿襟翼偏折两部分流动的增升效果简化模型,根据伯努利方程和楔形流理论得到增升效果计算公式,获得升力系数增加范围。在此基础上,研究了发动机尾部气流速度、机翼上表面面积和襟翼角度的影响效果。研究结果表明,机翼上表面吹气可以很好地改善飞机的低速性能,实现飞机短距起降。Using the high speed airflow of the engine installed on the upper surface of the wing to enhance the lift is an effective power lift enhancement technique. Without considering the influence of flow separation,a simplified model of the lift enhancement effect is established with two parts which are flow from the engine nozzle to the front of the flap and the deflection along the flap. According to the Bernoulli equation and the wedge-flow theory,the formula of the lift enhancement effect and the range of the increase in the lift coefficient are obtained. Based on this model,the effect of the airflow velocity of the engine exhaust,the area of the wing surface,and the flap angle on lift is studied. The results show that the low-speed performance of the aircraft can be improved by blowing air on the upper surface of the wing.

关 键 词：上表面吹气 动力增升 简化模型 短距离起降 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]