CFD Analysis of NACA2412 and NACA0012 at Low Reynolds (2.210*6) Numbers Based on ANSYS Fluent

The paper is about analysing two-dimensional aerodynamic characteristics of NACA 2412 and NACA0012 aerofoils at Reynolds number of 2.210*6 using the CFD method. Numerical analysis was performed through ANSYS Fluent, a fluid simulation software based on the finite volume method. The geometry model and mesh of the aerofoil are established by ANSYS Meshing, and the simulation calculation is carried out based on the pressure solver. During simulation processing, the Spalart Almaras model is used based on the incompressible continuity equation and Navier-Stokes Equation. The aerodynamic characteristics such as pressure, velocity distribution, CL and Cd, are systematically analysed and compared for these two airfoils. The results of the report show that if the aircraft needs to fly smoothly between 6-12, the NACA 0012 is a better choice and if you need to generate higher lift at low speeds, the NACA 2412 May be more suitable. The result of this paper can be applied to aircraft design, and new aerofoil development, and guide two-dimensional CFD analysis to these aerofoils.