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Use of wall suction in half model wind tunnel testing
conference contribution
posted on 2010-06-25, 10:47 authored by Abdullah Mailk, Peter RenderThe half model wind tunnel technique suffers from aerodynamic loses due to the
interaction of the tunnel wall boundary layer with the flow over the model and the formation
of a horseshoe vortex in the model-floor junction. The vortex is believed to contribute to the
degradation of the half model aerodynamic performance. An attempt was made to reduce
the aerodynamics losses by modifying the junction horseshoe vortex through the use of
localized suction just upstream of the model leading edge. Wind tunnel tests on a rectangular
and untwisted, wing only, modified LS(1)-0413 half model were conducted at Reynolds
numbers of 0.44 x 10(6), 0.88 x 10(6) and 1 x 10(6). Without suction the force and moment balance
measurements of the half model showed the anticipated deviation from full model values,
e.g. lower lift curve slope and higher drag values. Effects of localized suction were limited to
Reynolds number of 0.44 x 10(6) and improvements were seen only near stall angles of attack.
Flow visualization for the no suction case showed that a horseshoe vortex did not exist over
much of the incidence range for this particular model and hence there was little room for
suction to effect junction flow. Near stall, suction removed the horseshoe vortex around the
upper surface of the model and significantly reduced flow separations occurring in the
model-floor junction, leading to the improved stall characteristics.
History
School
- Aeronautical, Automotive, Chemical and Materials Engineering
Department
- Aeronautical and Automotive Engineering
Citation
MALIK, A. and RENDER, P.M., 2010. Use of wall suction in half model wind tunnel testing. 28th AIAA Applied Aerodynamics Conference, 28th June - 1st July 2010, Chicago, Illinois.Publisher
American Institute of Aeronautics and Astronautics (AIAA) / © The authorsVersion
- AM (Accepted Manuscript)
Publication date
2010Notes
This is conference paper, presented at the 28th AIAA Applied Aerodynamics Conference: http://www.aiaa.org/Language
- en