In the current scenario, Nano Air Vehicle (NAV) plays an indispensable role in both defence and civil applications significantly, such as earthquake, avalanche, low intensity conflict, spying, etc. The important features of NAV include low Reynolds Number, fluid-solid interaction, boundary layer separation and other parameters. This research work is the continuation of our previous work related to the aerodynamics of flexible flapper & passive stability (200 mm flying model) and fully unsteady

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... erodynamic analysis of 3D flapping wing MAV which executing translational motion. Based on the lessons learnt by the authors from their previous experience, this paper examines the relationship between the wake structures and the forces developed by a flapping airfoil, executes the lateral motion which is one of the fundamental researches towards the development of NAV. In the present paper, the unsteady aerodynamic analysis of 2D flapping airfoil (Lateral motion) is analysed by solving the 2D time-dependent incompressible Navier-Stokes equations for free stream velocity of 5 m/s which includes dynamic mesh techniques, user defined functions, low Reynolds number, flapping motion and geometry. Different methods for dealing with the moving boundary were evaluated using mesh deformation, re-meshing and optimization for unstructured grids. Additionally, the control parameters such as the flapping amplitude, reduced frequency and Strouhal number were also taken into the account. These studies are stepping stone towards the design and development of NAV (~ < 75 mm), flapping wing mechanism, 1D wavelet analysis and testing through NI systems.