微型飞机机翼平面布局的风洞试验研究  

Investigation on MAVs of Plan Configurations in Wind Tunnel

作　　者：肖国东[1] 宋笔锋[1] 李占科[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《科学技术与工程》2007年第10期2440-2442,共3页Science Technology and Engineering

基　　金：总装气动预研项目(413130401);国防基础科研项目(J1500C001)联合资助

摘　　要：介绍了常用的15种微型飞机机翼平面布局在西北工业大学低湍流度风洞进行风洞试验研究的情况。研究目的是探索微型飞机的风洞试验技术和获得各种微型飞机布局的低雷诺数气动特性。着重研究了风速、迎角对微型飞机各布局气动特性的影响。研究结果表明:风洞试验是研究与微型飞机有关的低雷诺数气动特性问题的有效而又切实可行的途经;八面形布局具有较高的升阻比和升力系数,是微型飞机理想的设计选择。试验结果可供微型飞机设计参考。The investigation of MAVs （Micro Air Vehicles） of several configurations were carried out in Low Turbulence Wind Tunnel at NPU （ Northwestern Polytechnical University）. The aim is to explore the experimental technique of the MAVs and obtain low Reynolds number aerodynamic characteristics on the configurations. The influence of wind velocity and angle of attack on aerodynamic characteristics is reported. It is shown that the wind tunnel experiment is an effective and feasible way to study low Reynolds number aerodynamic characteristics and octagonal configuration has higher lift-to-drag ratio and higher lift coefficient than the others. It is an ideal configuration choice for the design of the MAVs. The results of The tests can be used to refer to the design of MAVs.

关 键 词：微型飞机 低湍流度风洞 气动特性 低雷诺数 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] V211.74