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The present work investigates the effect of Reynolds number on NACA0012 aerofoils for various angles of attack on the aerodynamic characteristics both experimentally as well as numerically. The modifications in the flow, as well as aerodynamic characteristics of the NACA0012 aerofoil, are systematically compared using pressure coefficient, lift coefficient, vortex shedding, etc. The study was conducted for a chord wise Reynolds number of (a) 2.21 x 105 and (b) 2.81 x 105 at an angle of attack of 0deg, 5deg, 10deg, 15deg and 20deg. A large difference in the pressure coefficient is observed between the top and bottom surface in the case of lower Reynolds number and thus it indicates that at low Reynolds number high lift is generated than at high Reynolds number. L/D study also reveals that with increasing Reynolds number the NACA0012 aerofoil losses its lifting aerodynamics property. From the vortex plot, it is clear that leading edge shedding has a negative impact on the lift of the aerofoil for 2D simulation. Thus, this paper sufficiently demonstrates the effect of Reynolds number on the aerodynamic characteristics of the NACA0012 aerofoil.