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Wind Tunnel Test of a Blended Wing Aircraft in Ground Effect With Active Flow Control

[+] Author Affiliations
Michael Mayo, Jonathan Carroll, Nicholas Motahari, Warren Lee, Robert Englar

Georgia Tech Research Institute, Atlanta, GA

Paper No. IMECE2016-65683, pp. V001T03A038; 10 pages
  • ASME 2016 International Mechanical Engineering Congress and Exposition
  • Volume 1: Advances in Aerospace Technology
  • Phoenix, Arizona, USA, November 11–17, 2016
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-5051-0
  • Copyright © 2016 by ASME


This paper describes the test methodology and results for a wind tunnel experiment featuring a blended wing aircraft in ground effect with built-in circulation control. A 82.55cm wingspan blended wing model was tested in a subsonic wind tunnel at velocities ranging from 18m/s – 49m/s and corresponding Reynolds numbers ranging from 130k – 350k. Pitch angle was held constant at 0 degrees and the height above the wind tunnel floor was modified to determine lift and drag modification due to ground effect. At a normalized height (y/bw) of 0.06, ground effect increased lift production by 24% and reduced drag by 22% when compared to a normalized height of 0.5. The addition of the circulation control significantly increased the lift production of the model at a cost of increased drag. At a normalized height of 0.031, the lift production increased by 200% at a blowing coefficient of 0.01, but the drag also increased by 72%, ultimately increasing L/D by 178%. Experimental results also suggest that ground effect and circulation control have a synergistic effect when used simultaneously. The effects of Reynolds number and circulation control slot height are also investigated.

Copyright © 2016 by ASME



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