Unsteady flow past a plunging airfoil
نویسندگان
چکیده
This paper presents simulations of unsteady flow past a plunging airfoil using the highorder spectral difference (SD) method. Both third-order and fourth-order SD methods are used on unstructured quadrilateral grids. The vortex shedding pattern of an airfoil in an oscillating plunge motion becomes asymmetric at a sufficiently high frequency. The SD method is able to capture this effect and reveal a fine structure that closely replicates the experimental photographs, and which is not observed in lower order simulations. The algorithms could enable high-order accurate simulations of laminar flow past flapping Micro-Air-Vehicles (MAVs) with more complicated motions.
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