Marshall, D.W., Newman, S.J. and Williams, C.B.
Boundary layer effects on a wing in ground-effect
Aircraft Engineering and Aerospace Technology, 82, (2), . (doi:10.1108/00022661011053391).
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Experiments were carried out in the University of Southampton's 3x2 wind tunnel. A variable length splitter plate was designed and manufactured in order to generate four boundary layer thicknesses at a selected measurement position. A single element inverted GA(W)-1 aerofoil was then introduced to the flow at varying heights above the plate. Laser doppler anemometry and static surface static pressure measurements (both on the aerofoil and the splitter plate) were recorded.
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