Comparative Analysis of Aerodynamic Characteristics of NACA4412 and NACA23012 Airfoils at High Reynolds Number

Abstract

This study selects the NACA4412 and NACA23012 airfoils as research objects and conducts two-dimensional numerical simulations of their aerodynamic characteristics under a high Reynolds number condition of Re=1.9×10^6 using CFD-based fluid simulation software. The incompressible continuity and Navier–Stokes equations are solved via the finite volume method, combined with the k-ω SST turbulence model and a pressure-based solver. The lift coefficient, drag coefficient, and the distributions of pressure and velocity fields around the airfoils are systematically analyzed at attack angles of 0°, 6°, 12°, and 18°. The simulation results indicate that NACA23012 exhibits superior lift-to-drag characteristics and drag control capability within the low angle-of-attack range of 0–6°, while NACA4412 demonstrates higher lift potential and better lift sustainability within the high angle-of-attack range of 12–18°. The comparative analysis of the aerodynamic differences between the two airfoils provides data support for the selection and optimization of airfoils for aircraft operating under high Reynolds number conditions.