Enhanced Aerodynamic Characteristics using Higher Order Curved Convex and Concave Meshing for an Incompressible Flow Analysis over NACA Airfoil

Abstract

The present research work focuses on accurate aerodynamic computation and flow investigations of NACA 4-digit airfoil design to enhance the lift performance and consequently improve the efficient usage of fuel for commercial purposes of an aerodynamic device. For a cost-efficient airfoil shape, improved aerodynamic characteristic is essential, which has been computed efficiently by interpreting the effects of Reynolds numbers at different angles of attack. These aerodynamic parameters have been analyzed at various Reynolds numbers ranging from 10,000 to 1,000,000 (104 < Re < 106). This study employs an inventive approach to mesh generation, employing higher order triangular elements to encompass the NACA 0012 airfoil design, utilizing subparametric finite elements for enhanced accuracy and efficiency. It facilitates precise data of the boundary node information of the NACA 0012 airfoil design which has been utilized for the excellent computation of lift and drag coefficient, and the lift-to-drag ratio and can reduce the hardships of aerospace research associated with flow analysis. The pressure exerted around the airfoil surface has been investigated for Reynolds number 2×104 at the angle of attack of 5° The present work also delineates the understanding of the effects of boundary layer flow behavior on airfoil design utilized for aircraft, helicopters etc. at different Reynolds numbers. The present computation is helpful to design an optimized airfoil shape for better lift performance and manufacture a fuel-efficient aerodynamic device for aerospace applications.