Evaluation of wing performance for NACA 4415 using subparametric finite element transforms

The goal of the current research is to improve the lift performance of an aerodynamic device for commercial application by performing accurate aerodynamic computations and flow analyses of NACA 4-digit airfoil designs. An enhanced aerodynamic characteristic, which has been estimated effectively by interpreting the impacts of Reynolds numbers at various angles of attack, is crucial for a cost-effective airfoil shape. Numerous Reynolds numbers have been used in the analysis of these aerodynamic properties. Investigations were carried out using subparametric finite elements and a unique approach for higher order triangular element meshing in relation to the NACA 4415 airfoil design. This approach provides precise boundary node information for the airfoil design, resulting in improved calculations of the lift coefficient, drag coefficient, and lift-to-drag ratio. Moreover, it effectively addresses the challenges faced in aerospace research pertaining to flow analysis, thereby reducing the complexities involved. The evaluationof the airfoil shape and analysis for incompressible flow over the NACA 4415 airfoil design could improve the overall effectiveness of the aerodynamic vehicle. Any vehicle's aerodynamic surface must go through a number of tests before being launched. Modern technology can be incorporated into the design process to reduce the high costs associated with these testing processes. The current flow analysis and aerodynamic investigations exhibit a high degree of accuracy, and the use of HO elements lowers the expense of the experiment.