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oai:www.ideals.illinois.edu:2142/14616 2023-07-10 col_2142_5131 col_2142_14800 com_2142_5130 com_2142_14799 com_2142_234

Selig, Michael S. Selig, Michael S. Bishop, Nathan F. 2010-01-06T16:19:48Z 2010-01-06T16:19:48Z 2010-01-06T16:19:48Z 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. Item withdrawn by Mark Zulauf (zulauf@illinois.edu) on 2009-11-16T19:43:18Z Item was in collections: University of Illinois Theses & Dissertations (ID: 1) No. of bitstreams: 1 Bishop_Nathan.pdf: 7659573 bytes, checksum: 98bb7ead0d274953dfa204179e75c945 (MD5) 2009-12 Made available in DSpace on 2010-01-06T16:19:48Z (GMT). No. of bitstreams: 2 license.txt: 4063 bytes, checksum: a6ac62a2a54501102c575578f9db035b (MD5) Bishop_Nathan.pdf: 7659573 bytes, checksum: 98bb7ead0d274953dfa204179e75c945 (MD5) http://hdl.handle.net/2142/14616 en Copyright 2009 Nathan F. Bishop low reynolds number water tunnel experimental aerodynamics micro aerial vehicles nano aerial vehicles force balance design wing performance Measurements of Wings at Very Low Reynolds Numbers Aerospace Engineering 1615 Aerospace Engineering 4048 University of Illinois at Urbana-Champaign Thesis M.S. MS: Aerospace Engr -UIUC 10KS4048MS