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This paper deals with the investigation of flow field due to clap and flingmechanism using immersed boundary coupled with lattice Boltzmann method. Thelattice Boltzmann method (LBM), an alternative to Navier Stokes solver, is usedbecause of its simplicity and computational efficiency in solving complexmoving boundary problems. Benchmark problems are simulated to validate thecode, which is then used for simulating flow over two elliptic wing of aspectratio 5 performing clap and fling flapping motion for different flow parameterssuch as Reynolds number (Re = 75,100,150), advance ratio (J = 10E-3,10E-2,2)and frequency (f = 0.05Hz,0.25Hz). Numerical simulation is able to capturetypical low Reynolds number unsteady phenomena such as, 'wake vortex winginteraction', 'Kramer effect' and 'delayed stall'. The results are bothqualitatively and quantitatively consistent with experimental observation. Theparametric study involving different combinations of Re, f and J depictdistinctly different aerodynamic performances providing physical insights intothe flow physics. It is observed that a combination of low f, low J and high Reflow results in better aerodynamic performance. Pronounced lift enhancement vialeading edge vortices are obtained in unsteady regime (J<1) compared toquasi-steady regime (J>1). The role of leading edge vortices in enhancing liftare investigated by studying the size and strength of these vortices fordifferent flow conditions. For a given Re, the magnitude of maximum liftcoefficient decreases with increasing f irrespective of the value of J; whilethe same is enhanced with the increasing Re.

Investigation of flow field of clap & fling motion using immersed boundary coupled lattice Boltzmann method