基于涡格法的近程无人机气动优化与风洞实验验证  

Aerodynamic optimizaiton for short range UAV using vortex lattice method and wind tunnel verification

作　　者：李大伟[1] 阎文成[2] 江峰[2] 

机构地区：[1]北京航空航天大学无人驾驶飞行器设计研究所,北京100191 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2012年第3期61-65,共5页Journal of Experiments in Fluid Mechanics

摘　　要：针对低雷诺数的近程无人机,利用涡格法(VLM)对无人机气动特性进行了加装翼尖小翼优化设计,并通过风洞实验进行了验证。首先给出了翼尖小翼的几何参数并分析其对全机气动特性的影响,其次利用涡格法对小翼进行气动建模和优选,针对无人机巡航状态给出了小翼优化结果,最后利用风洞实验对优化前后的无人机进行了吹风实验对比验证,实验结果表明,涡格法和风洞实验结果在线性段相符,涡格法能够较准确地描述和预测翼尖小翼特性,加装翼尖小翼后的无人机巡航状态升阻比提高12%,全机滚转阻尼加大,偏航阻尼变化很小。According to the aerodynamic geometry of the UAV that operates at low Reynolds number, winglet was designed to improve the efficiency of the UAV hy using vortex lattice meth- od（VLM）. Optimized designs were validated by wind tunnel tests. First, several key parameters were analyzed for winglet design. Second, the optimized winglet was obtained by the VLM for UAV at cruising state. Last, a wind tunnel test for the UAV with and without winglet was car- ried out. Based on comparison of VLM results to full scale measured wind tunnel test data, it can be seen that they match well during linear segment. It means that the winglet was designed prop- erly using VLM thus the lift to drag ratio of the UAV was increased by 12%, and the roll damp- ing was increased but the yaw damping was not changed, on the other hand, these results should provide valuable guidance in designing winglet for UAV by using VLM.

关 键 词：低雷诺数 翼尖小翼 涡格法 风洞实验 无人机 

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]