Paper Title
Prediction of Propulsion in a Low Thickness to Chord Ratio Flapping Rectangular Foil

Abstract
Recently, researchers and scholars have been affianced in a more profound examination of insect flight as it speaks to one of the nature's best case of species presented with amazing mobility and route abilities and that has motivate analysts to plan smaller scale air vehicles (MAVs) on a comparable idea. In any case, the avian fluttering flight includes complex liquid wonders that don't pursue the traditional quasi-steady hypotheses pervasive in fixed wing optimal design. Besides, the logical comprehension of how linear stability influences mechanics and propulsive execution of a rigid plunging wing is a long way from complete, particularly concerning the change in flow structure around plunging wings which happen to be detached. Consequently, here we emulate a genuine rigid plunging wing utilizing a liquid structure collaboration system. The developed fluid and auxiliary solvers together decide the aerodynamicforces on wing. The liquid solver utilizes a novel translating continuous-grid-block model for moving limits of limited thickness dependent on multi-relaxation time variant of Boltzmann technique. A portion of the key parameters distinguished to assume a significant job in the propulsive execution are the flapping Reynolds number Ref , membrane thickness  , natural non-dimensional parameters: amplitude or Keulegan-Carpenter number (KC) and frequency or Stokes number (β). Numerical simulation are performed on a rigid foil to portray the impact of these parameters on the symmetry breaking that will onset of forward propulsion and centre of mass trajectory of foil at the different locations on transition boundary in KC-β space. Keywords - Lattice Boltzmann; Rigid Plunging Wing; Floquet Stability Analysis; Eigenvalue Problem; Laminar Flow.