Aerodynamic Characteristics of NACA2412 and NACA4412 at Low Reynolds Number Numerical Simulation

The aerodynamic performance of airfoils cannot only optimize the lift and drag control of the aircraft to improve the overall performance of the aircraft but also can provide technical support for new concept airfoils, such as bionic airfoil optimization, adaptive deformation wings. However, due to the long cycle of experimental research and the inability to quickly iterate, there are few systematic comparative analyses of such airfoils. Therefore, this paper primarily investigates the two-dimensional aerodynamic characteristics of NACA2412 and NACA4412 at various angles of attack at a Reynolds number of 2.2 10^6. ANSYS Fluent was used for geometric modelling and grid division, and the simulation calculation was carried out by using the K- SST model and pressure-based solver. The simulation results show that NACA4412 can produce a larger lift coefficient in the range of 0 -12 of the angle of attack. The stall angle of NACA2412 is 16 , and the stall curve is gentle, while the stall angle of NACA4412 is 13, and the curve after the stall is steep. Through the systematic comparative analysis of the aerodynamic characteristics of both, it can provide a reference for the subsequent airfoil design and optimization.