Measurements of Wings at Very Low Reynolds Numbers

low reynolds number;water tunnel;experimental aerodynamics;micro aerial vehicles;nano aerial vehicles;force balance design;wing performance

Bishop, Nathan F. ; Selig, Michael S. ; Selig ; Michael S.

关键词: low reynolds number;    water tunnel;    experimental aerodynamics;    micro aerial vehicles;    nano aerial vehicles;    force balance design;    wing performance;   

Others  :  https://www.ideals.illinois.edu/bitstream/handle/2142/14616/Bishop_Nathan.pdf?sequence=2&isAllowed=y

美国|英语

来源: The Illinois Digital Environment for Access to Learning and Scholarship

【 摘 要 】

Very low Reynolds number aerodynamics is a rapidly growing field of interest, especiallyin regard to the design and development of micro- and nano-air vehicles. In the workculminating in this thesis, force measurement apparatuses were designed and prototyped tomeasure wing performance at very low Reynolds numbers in a water tunnel. The lift anddrag behavior for rectangular wings with discretely angled wing profiles and aspect ratiowere obtained at Reynolds numbers between 4,000 and 10,000. This thesis is intended toinform both future force measurement apparatus development for water tunnel applicationsand experimental research in wing performance at very low Reynolds numbers.