We performed wall-modeled large-eddy simulation of the flow field around the VFE-2 delta wing, focusing on two aspects: (1) leading-edge bluntness effects on the primary vortex separation and (2) vortex breakdown above the wing and its control. Regarding aspect (1), the VFE-2 delta wing with sharp leading-edge (SLE) and medium radius round leading-edge (MRLE) are considered for three angles of attack α (13°, 18°, and 23°) leading to different overall flow characteristics. The numerical simulations correctly predict the main flow phenomena and are quantitatively in reasonable to good agreement with experimental measurements of steady and unsteady surface pressures, velocity distributions, and vortex breakdown position and frequency. Regarding aspect (2), flow control by oscillating control surfaces and flow control by a geometric modification leading to an injection of fluid from the pressure side are investigated for the SLE at α = 28°. Considering the influence on vortex breakdown position, the numerical simulations confirm experimental observations regarding oscillating control surfaces, and show promising potential for flow control.
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