Abstract
This study focuses on the corner flow separation occurring in a simplified wing-body junction composed of a NACA0015 twisted wing mounted on a flat plate at a Reynolds number based on the wing chord of . Wind-tunnel test measurements are carried out in the corner area including extensive oil-flow visualizations, high speed particle image velocimetry and unsteady pressure sensors. The analysis of the experimental database shows that the corner flow separation creates mean flow distortions that induce high anisotropy in the Reynolds stresses and turbulent kinetic energy. The wall pressure spectra show a broadband hump associated with the corner flow separation at , based on the incoming boundary layer thickness. A sensitivity study indicates the progressive growth of the corner flow separation with increasing angle of attack, leading to complete wing stall and the delay of the corner flow separation onset when the incoming boundary layer is thicker.
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