Publication

Abstract : The primary objective of this computational research is to investigate on the effects of Reynolds number, angle of attack, frequency, and amplitude of the plunging movement of NACA0012 airfoil on aerodynamic performance over time for a constant angle of attack. This paper deals with the laminar flow over the plunging NACA0012 airfoil at low Reynolds number 10000 with a plunging amplitude ratio of 0.2c and with three different frequency ratios of 0.9, 1.0, and 1.1. The influence of the angle of attack {constant over time} was studied in the range of 0 to 6. OpenFOAM an open-source CFD software is used to simulate this problem computationally.