低雷诺数小型无人飞机气动设计  

Small Unmanned Aerial Vehicle Aerodynamic Design of Low Reynolds Number

作　　者：马献伟[1,2] 白俊强[1] 

机构地区：[1]西北工业大学航空学院 [2]中国人民解放军91395部队

出　　处：《航空计算技术》2012年第6期17-20,24,共5页Aeronautical Computing Technique

基　　金：总装备部预先研究项目资助(51325060301)

摘　　要：讨论了当前固定翼小型无人驾驶飞行器(SUAV)的发展。分析了低雷诺数的空气动力特性,包括分离气泡和展弦比的影响。根据设计性能指标,进行总体参数估算,完成了两种方案的外形设计,分别采用了常规式和飞翼式的布局形式,由此进行了不同的低雷诺数翼型和机翼配置,并对设计结果进行了气动分析。讨论了两种布局形式的优缺点,包括起降性能、稳定性,完成了总体气动方案的初步设计。The current development of small unmanned aerial vehicles （SUAV） by the platform of fixedwing is discussed. The aerodynamic characteristics of low Reynolds number, and the influence to laminar separation bubble and aspect ratio are analyzed. According to the design performance target, the overall parameters are estimated and the shape design of two designs are completed. Normal and flying wing lay- out is respectively applied. Then the different airfoil and wing with low Reynolds number are used and the aerodynamic analysis of the result is achieved. The advantages and disadvantages of two layout forms are discussed, including take- off and landing performance and stability, the overall aerodynamic design scheme is completed.

关 键 词：小型无人驾驶飞行器 气动设计 低雷诺数 层流气泡分离 展弦比 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]