摘要
用于微型飞行器气动特性研究用的极低速风洞在国外公开发表的资料很少见到。因此在总体设计、气动计算与结构设计中均遇到许多新问题。在缺少资料以及实际设计与使用经验的情况下,经过多方案比较、详细的气动计算、调查研究和实机测试,按照设计技术要求研制成功了试验段直径为100mm,风速可以从1m/s无级调速到13m/s的微型飞行器研究用极低速开口自由射流风洞。其流场可用区域大,流速可调范围宽,而且可以无级调速。给出了总体方案的选择、部件气动计算的结果、风洞气动轮廓图以及流场测量数据。
Papers about ultra-low speed wind tunnels for aerodynamic characteristics research on Micro UAV are scarce. Many new problems are appeared in general design, aerodynamic computing and structural design. After comparing a few projects, computing in detail, investigation and measuring for wind tunnel, a ultra-low speed wind tunnel is designed successfully. It is an open free jet wind tunnel for research on Micro UAV. The diameter of test section is 100mm, and the velocity can be changed continuously from 1m/s to 13m/s. This paper gives the selection of general project, the results of aerodynamic computing for pans, the sketch of wind tunnel as well as the data of flow measured in the wind tunnel.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2006年第1期58-61,共4页
Journal of Experiments in Fluid Mechanics
关键词
微型飞行器
极低速风洞
气动计算
Micro-UAV
ultra-low speed wind tunnels
aerodynamic computing
