Studies on vortex flaps with rounded leading edges for supersonic transport configuration

Wind-tunnel measurements were taken on a cranked arrow wing supersonic transport configuration with leading-edge vortex flaps. Force and surface pressure measurements were made at Reynolds number based on the wing mean aerodynamic chord from 9.2 × 105 to 3.8 × 10 6 . Two different flap cross sections (the originally designed nonrounded leading edge and the rounded leading edge) were tested. The purpose of the measurements is to clarify how the differences of the Reynolds number affect the flow around the rounded leading-edge vortex flaps and the flap performance. The wing with the rounded leading-edge vortex flaps indicated some benefit of the lift/drag ratio as compared with those of the nonrounded vortex flaps at a relatively high-lift coefficient greater than 0.3

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