Three-Dimensional Effects on Plunging Airfoils at Low Reynolds Numbers

Abstract

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Fluid-structure interaction of multi-body systems: Methodology and applications

“…For further details on the immersed boundary method described above, the reader is referred to Uhlmann [12]. This algorithm has been implemented in a flow solver called TUCAN, which has been successfully used for the simulation of rigid-bodies with prescribed kinematics [40,41,42,43,44,45]. Likewise, the free motion of a single-rigid body immersed in a fluid has been also successfully simulated [46,47], using the coupling method presented in Uhlmann [12].…”

Characterization of Aerodynamic Forces on Wings in Plunge Maneuvers

“…Perrotta and Jones [15] performed an extensive parametric study by varying velocity ratio, , duration of the maneuver, , and angle of attack of the wing, . In the present study, due to the high computational cost of the direct numerical simulations, we focus on a small set of parameters driven by the previous study of Moriche et al [17]. We fix the duration of the maneuver = 2 / ∞ so that the width is also fixed, / = 2, and the height depends on the velocity ratio, ℎ/ = .…”

“…The grid is uniform in the vicinity of the airfoil (−0.5 < / < 2.5, −2.5 < / < 0.5). The grid resolution in this region was defined after performing a grid refinement study in 2D simulations as reported by Moriche et al [17], resulting in a grid spacing in all three directions of Δ = /320. Far from the airfoil along the and directions the grid is stretched using a 1% stretching, except upstream where a 3% stretching is used.…”

“…The curves of for both experiments and simulations are shown in Figures 3a-b. Moriche et al [17] divide the time evolution into three intervals. The first interval is the acceleration phase, 0 ≤ ∞ / ≤ 1, where the grows rapidly until a peak is reached at an instant before the end of the interval.…”

“…Forces were measured for a large variety of plunge maneuvers, varying the width and height traveled by the wing during the maneuver as well the geometric angle of attack of the wing. Moriche et al [17] performed direct numerical simulations (DNS) using some of the kinematics of Perrotta and Jones [15], but for a model of an infinite aspect-ratio NACA0012 wing. The lift coefficient predicted in the simulations was found to be in qualitative agreement with the measurements, however, some quantitative discrepancies were observed.…”