Numerical Simulation Study of the Aerodynamic Performance of Two Different NACA Airfoils

Abstract

This paper conducts two-dimensional numerical simulation experiments on NACA0012 and NACA2412 wing profiles, using a two-dimensional coordinate system to simulate wing profile data and generate structured grid computing domains and aircraft wing profile meshes centered around the wing profile. Computer simulation software simulates every 4° between 0° and 20° at a speed of 33 m/s. The pressure cloud diagrams and flow velocity cloud diagrams of the two airfoil types, as well as changes in lift coefficients and drag coefficients. The results show that the symmetric wing structure design used in NACA0012 has a smaller difference in airflow velocity between the upper and lower surfaces over a small angle of attack, offering better stability and suitability for maneuverable aircraft. The surface of NACA2412 can achieve higher flow rates and greater lift. At the same angle of attack, NACA2412 experiences less resistance than NACA0012, provides greater lift, and offers a better lift-to-drag ratio.The lift of the two wing types primarily affects the front end of the upper wing, with pressure centers gradually concentrating forward. Wake expansion generates turbulence that interferes with the upper wing airflow, reducing lift and causing stall.