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Title:Measurements of Wings at Very Low Reynolds Numbers
Author(s):Bishop, Nathan F.
Advisor(s):Selig, Michael S.
Contributor(s):Selig, Michael S.
Department / Program:Aerospace Engineering
Discipline:Aerospace Engineering
Degree Granting Institution:University of Illinois at Urbana-Champaign
Subject(s):low reynolds number
water tunnel
experimental aerodynamics
micro aerial vehicles
nano aerial vehicles
force balance design
wing performance
Abstract:Very low Reynolds number aerodynamics is a rapidly growing field of interest, especially in regard to the design and development of micro- and nano-air vehicles. In the work culminating in this thesis, force measurement apparatuses were designed and prototyped to measure wing performance at very low Reynolds numbers in a water tunnel. The lift and drag behavior for rectangular wings with discretely angled wing profiles and aspect ratio were obtained at Reynolds numbers between 4,000 and 10,000. This thesis is intended to inform both future force measurement apparatus development for water tunnel applications and experimental research in wing performance at very low Reynolds numbers.
Issue Date:2010-01-06
Rights Information:Copyright 2009 Nathan F. Bishop
Date Available in IDEALS:2010-01-06
Date Deposited:December 2

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