Flight experiments on the effects of step excrescences on swept-wing transition
by Glen T. Duncan Jr.; Brian K. Crawford; Matthew W. Tufts; William S. Saric; Helen L. Reed
International Journal of Engineering Systems Modelling and Simulation (IJESMS), Vol. 6, No. 3/4, 2014

Abstract: A 30° swept-wing model with a movable, leading-edge extending to 15% chord is used in flight tests to study the effect of two-dimensional, step excrescences on swept-wing transition, where stationary-crossflow waves are typically the dominant instability. Transport unit Reynolds numbers are achieved using a Cessna O-2A Skymaster. Forward- and aft-facing steps are modulated in-flight. Pressure measurements are compared with CFD. Infrared thermography is used to globally detect boundary-layer transition. When the 2-D pressure gradient matches the unswept case, the swept-wing case has a lower _Rekk,crit. However, there is still potential to relax conventional, laminar-flow tolerances for steps.

Online publication date: Sat, 26-Jul-2014

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