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Experiments on the Velocity Field Around a Low Aspect Ratio Wing at Low Reynolds Numbers

[+] Author Affiliations
Daniel R. Morse, James A. Liburdy

Oregon State University, Corvallis, OR

Paper No. IMECE2009-13172, pp. 393-406; 14 pages
  • ASME 2009 International Mechanical Engineering Congress and Exposition
  • Volume 9: Heat Transfer, Fluid Flows, and Thermal Systems, Parts A, B and C
  • Lake Buena Vista, Florida, USA, November 13–19, 2009
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-4382-6 | eISBN: 978-0-7918-3863-1
  • Copyright © 2009 by ASME


The flow structure around a low aspect ratio wing at low Reynolds numbers and a fixed angle of attack of 20° is discussed using flow visualization as well as Three-Component Time-Resolved Particle Image Velocimetry (3C TR PIV). Mean quantities and statistical measurements of velocity were obtained and used to describe the average and transient characteristics of the flow field. Effects of spanwise variation from centerline to wingtip and Reynolds number variation from 1.3×104 to 6.6×104 are discussed. The role of the wing tip vortices is observed to be large in a low aspect ratio wing. The transfer of momentum via Reynolds shear stresses is shown in the leading edge region. Normalized spanwise shear stresses associated with the wing tip vortices are observed to increase with increasing Reynolds number.

Copyright © 2009 by ASME



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