翼尖小翼对尾涡安全间隔的影响研究  

Research on calculating the effect of winglets on aircraft safety spacing of wake vortex

作　　者：魏志强[1,2] 刘菲[1] 刘薇[1,2] 

机构地区：[1]中国民航大学空中交通管理学院,天津300300 [2]天津市空管运行规划与安全技术重点实验室,天津300300

出　　处：《飞行力学》2014年第2期101-104,共4页Flight Dynamics

基　　金：国家自然科学基金资助(61179042);中央高校基本科研业务费项目(CAUC-ZXH2010D013);中国民航大学科研基金资助(08CAUC-E08)

摘　　要：飞机加装翼尖小翼后可降低翼尖涡的强度，在减少飞机诱导阻力、提高飞行经济性的同时也会降低飞机的尾涡强度，有利于缩减尾涡安全间隔。通过对加装翼尖小翼后飞机低速极曲线的拟合研究，分析了诱导阻力的变化情况，进而提出用当量展弦比来反映翼尖小翼对尾涡涡强度的影响。然后以B737-800和B737-800W飞机的气动原始数据为例，进行了计算分析。结果表明，加装翼尖小翼后的飞机在起降阶段的阻力系数减小量在3％左右，等价于飞机的展弦比提高了4．96％，从而可以降低4．73％的尾涡初始强度，使得相同气象条件下对后机的诱导力矩系数降低约6％～8％，尾涡安全间隔则可以减小3．5％左右。Winglets can be used to reduce the strength of wing tip vortex. With the decrease of induced drag and increase of flight economy, the strength of wake vortex can be decreased by this technology. The change of induced drag is analyzed through the research of low-speed drag polar curves when the winglets are installed. Then the equivalent aspect ratio was proposed to reflect the effect of winglets on vortex strength of the wake vortex. After that, the initial aerodynamic data of B737-800 and B737-800W were used to calculate the difference, which shows that the winglets can cause the decrease of 3% of the in- duced drag coefficient. As a result, the equivalent aspect ratio is 4. 96% higher than the real aspect ratio, and the initial strength of wake vortex is decreased by 4. 73%, thus the induced moment coefficient of the following aircraft is decreased by 6% - 8%, and the safety spacing of wake vortex is decreased by about 3.5% in the same weather condition.

关 键 词：尾涡安全间隔 气动分析 翼尖小翼 当量展弦比 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]