摘要
针对某型无人机大展弦比折叠机翼展开过程,对其缩比模型在不同迎角、不同机翼掠角状态下的气动特性进行了风洞实验。实验结果表明,布局的气动外形满足巡航设计要求,纵向与横航向稳定性较好,多面组合式机身表面可为全机升力带来有利影响,研究结果可在无人机、巡飞导弹等研究领域得到应用。
According to the deployment process of high-aspect-ratio UAV floding wings, aerodynamic characteristics is studied on scaled model at different attack angle and different grazing angle for wind tun- nel test. Experimental results show that layout of aerodynamic configuration can meet design requirements of cruise, and it has a good stability at vertical and transverse course. Multi-surface combined Fuselage can bring favorable effect on full-aircraft. Characteristic analysis points out the direction of aerodynamic shape optimization. Results can be applied in the research areas of UAV and loiter attack missile.
出处
《飞行力学》
CSCD
北大核心
2013年第1期80-83,共4页
Flight Dynamics
关键词
展弦比
气动特性
风洞实验
aspect-ratio
aerodynamic characteristics
wind tunnel test
