Aerodynamic Performance Evaluation of the NACA 65-421 Airfoil Using CFD and the k-ω SST Turbulence Model

Abstract In this study, the k-ω shear stress transport turbulence model is used to conduct a comprehensive computational fluid dynamics (CFD) analysis of the aerodynamic properties of the NACA 65-421 airfoil. Key parameters, including pressure distribution, velocity profiles, turbulence intensity, and lift and drag coefficients, are examined. The analysis is performed at a flow velocity of 22 m/s, and the simulation results are validated against experimental data. A significant pressure difference is observed in the pressure coefficient distribution, which contributes to effective lift generation. The observed drag remains relatively low, indicating minimal resistance to airflow. Analysis of turbulent kinetic energy reveals reasonable turbulence levels with sustained attached flow. The lift and drag data from simulations closely align with experimental findings, confirming the suitability of the k-ω shear stress transport model for predicting the airfoil’s aerodynamic characteristics. Further testing is recommended for the NACA 65-421 airfoil due to its low drag and effective lift, making it suitable for a range of aerodynamic applications.