摘要
端板偏转角α是影响联翼布局气动特性的主要因素,为了降低偏转角对联翼布局气动性能的影响,对端板的偏转角度设计了试验方案。基于CFD计算对机翼模型进行数值仿真,分析不同偏转角α下的升阻比和俯仰力矩特性。试验结果表明:在外倾角和纵向夹角不变的情况下,偏转角α=8°时,联翼布局的升阻比高且静稳定性好。研究结果可以为联翼布局设计提供一定的参考。
Deflection angle is the main factor affecting the aerodynamic characteristics of the wing layout.In order to reduce the influence of the deflection angle on the aerodynamic characteristics of the wing layout,the experimental scheme of the deflection angle parameter design of the end plate in the wing layout has been simulated.The CFD method is used to simulate the model and analyze the lift-to-drag ratio and pitching moment characteristics.The experimental results show that when the camber angle and the longitudinal angle are 0°,when the deflection angle is 8°,the joint-wing layout has a high lift-to-drag ratio and good static stability.The research results can provide a theoretical basis for the joint layout design and promote the development of the joint wing layout.
作者
龙纯毅
马尧
岳源
田顺
LONG Chun-yi;MA Yao;YUE Yuan;TIAN Shun(School of Aeronautical Engineering,Civil Aviation Flight University of China,Guanghan Sichuan 618307,China)
出处
《装备制造技术》
2019年第11期85-88,共4页
Equipment Manufacturing Technology
基金
中国民用航空飞行学院大学生创新训练项目(201710624029)
关键词
联翼布局
端板
偏转角
气动优化
joint wing aircraft
end plate
deflection angle
aerodynamic optimization
