| 微型飞行器研究用极低速风洞的特点 |
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| 引用本文： | 孙勇堂,朱孝业.微型飞行器研究用极低速风洞的特点[J].实验流体力学,2006,20(1):58-61. |
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| 作者姓名： | 孙勇堂 朱孝业 |
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| 作者单位： | 航天空气动力技术研究院,北京,100074 |
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| 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。
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| 关 键 词： | 微型飞行器 极低速风洞 气动计算 |
| 文章编号： | 1672-9897（2006）01-0058-04 |
| 收稿时间： | 2005-01-27 |
| 修稿时间： | 2005-06-31 |
Characteristics of ultra-low speed wind tunnels for research on Micro-UAV |
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| SUN Yong-tang,ZHU Xiao-ye.Characteristics of ultra-low speed wind tunnels for research on Micro-UAV[J].Experiments and Measur in Fluid Mechanics,2006,20(1):58-61. |
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| Authors: | SUN Yong-tang ZHU Xiao-ye |
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| Institution: | China Academy of Aerospace Aerodynamics, Beijing 100074, China |
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| Abstract: | 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 parts,the sketch of wind tunnel as well as the data of flow measured in the wind tunnel. |
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| Keywords: | Micro-UAV ultra-low speed wind tunnels aerodynamic computing |
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