Abstract
A study into the effects of forcing boundary layer transition on the suction surface of a GA(W)-1 section wing was undertaken using roughness-type boundary-layer trips. The wing was tested at a range of ground clearances with trips placed at varying chordwise locations using both numerical and experimental techniques. It was shown that forcing transition eliminated the occurrence of a laminar separation bubble, reduced circulation, and caused trailing-edge separation, which was dependent on trip location, to occur. The point of maximum downforce was also found to occur at lower ground clearances in forced-transition cases.
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