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Spanwise gradients in flow speed help stabilize leading-edge vortices on revolving wings

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Academic year: 2021

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Figure

FIG. 1: (Color online) Top view of the three configurations (A,B,C) used for the simulations
FIG. 4: (Color online) Circulation Γ of the LEV against dis- dis-tance δ traveled by the wing
FIG. 6: (Color online) Mean spanwise velocity V z Σ of the LEV against distance δ traveled by the wing
FIG. 7: (Color online) Lift coefficient C L against distance δ traveled by the wing. C L is obtained for cases A (plain), B (dashed) and C (dash-dotted) by non-dimensionalizing the lift force of the wing using the mean wing speed along the span V f ∞ .

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