无人机翼尖小翼参数优化及风洞试验研究  

Data Optimization and Wind Tunnel Test of UAV Winglets

作　　者：吴希拴[1] 师小娟[1] 王建培[1] 

机构地区：[1]西北工业大学无人机所,陕西西安710072

出　　处：《飞行力学》2004年第1期30-32,36,共4页Flight Dynamics

摘　　要：为延长无人机留空时间,加大航程和提高升限,可采用加装翼尖小翼的方法使无人机的升阻比有所提高。在工程估算的基础上,对几十种翼尖小翼的组合方案进行了风洞试验,并对试验结果进行了优化分析,得出了可供无人机使用的翼尖小翼参数。试验结果表明,加装翼尖小翼使全机最大升阻比可提高10.6%。Modification of winglet is adopted to raise the lift-drag ratio of the UAV for extension endurance,for enlarge range and for increase ceiling.Dozens of winglet models are investigated in the wind tunnel,which are based upon various engineering estimations.And test data obtained are optimized to apply to the engineering of a practical UAV.The experiment results showed that the maximum lift-drag ratio of the entire UAV increased by 10.6% winglet improvement.

关 键 词：无人驾驶飞机 翼尖小翼 参数优化 风洞试验 升阻比 

分 类 号：V224.4[航空宇航科学与技术—飞行器设计] V211.74