两种布局微型飞机的风洞试验研究  

The investigation on MAVs of two configurations in wind tunnel

作　　者：李占科[1] 宋笔锋[1] 张亚峰[1] 肖国东[1] 白存儒[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《实验流体力学》2006年第1期72-74,共3页Journal of Experiments in Fluid Mechanics

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：介绍了齐默尔曼和反齐默尔曼两种布局的微型飞机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两种布局微型飞机的低雷诺数气动特性。着重研究了风速、迎角对两种布局微型飞机气动特性的影响。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;反齐默尔曼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 two configurations were carried out in Low Turbulence Wind Tunnel at NPU （Northwestern Polyteclmical University）. The aim is to explore the experimental technique of the MAVs and obtain low Reynolds number aerodynamic characteristics on two 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 Inverse Zimmerman configuration has higher lift-to-drag ratio and higher lift coefficient than that of Zimmerman configuration. 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 齐耿尔曼布局 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程] V211.74