Numerical Analysis of Aerodynamic Performance Characteristics of NACA 2412 and NACA 4412 at Re = 4000000

This paper conducts a numerical analysis of the two-dimensional aerodynamic characteristics of the NACA 2412 and NACA 4412 aerofoils at a Reynolds number of Re = 4×106. Employing the fluid simulation software Ansys Fluent, which is based on the finite volume method, for numerical analysis. Both the geometric model and mesh of the aerofoil are established by using Fluent Meshing, and the simulation calculation is performed based on the pressure solver. Based on the Navier-Stokes equations, the SST k-ω turbulence model and coupled algorithm are employed for the simulation processing. The paper systematically compares the aerodynamic characteristics of NACA 2412 and NACA 4412, including the pressure and velocity distributions, as well as the variations in the lift coefficient, drag coefficient, and lift-to-drag ratio concerning the angle of attack. The results indicate that at Re = 4×106, the peak value of the lift-to-drag ratio of the NACA 2412 aerofoil is attained under the 8° condition, for the NACA 4412 aerofoil, the lift-to-drag ratio reaches its peak value at a 6° angle of attack. Additionally, the stall angles of both types of aerofoils under the studied operating conditions are 16°.