Wind energy has gained significant popularity as a renewable energy source, with horizontal axis wind turbines (HAWTs) being widely used for its efficient capture. The performance of HAWTs is greatly influenced by the design of their aerofoil blades, which convert wind energy into mechanical energy. To explore improvements in aerofoil aerodynamic properties, a basic research study was conducted using computational analysis. The study focused on the impact of different types of grooves on the surface of the NACA 23021 aerofoil. These grooves have the potential to enhance lift, reduce drag, and improve the stability of the aerofoil by promoting a more uniform pressure distribution. The grooves induce vortices in the fluid flow, enabling modification and control of flow direction and speed. This can lead to increased lift and decreased drag. Pilot studies on the 5-series aerofoil demonstrated reduced lift and drag coefficients at higher angles of attack (14°, 16°, 18°), with stall observed at 13° angle of attack (AOA). The study employed a segregated, implicit solver, k-ε SST model in ANSYS Fluent 2020. Unlike most published simulations, a multiblock organized grid was utilized, providing better accuracy, and capturing the curvatures of the leading and trailing edges through structured grid implementation. Analysis was conducted at 14°, 16°, and 18° angles of attack, considering parameters such as the ratio of boundary layer thickness (δ) to groove depth (h) (h/δ: 0.5–1.0) and groove depth (h) to groove width (d) ratio (h/d: 0.1–1). Among these conditions, the best improvement in lift-to-drag ratio, reaching 15.3%, was achieved at h/δ  = 1.0, h/d = 0.2, and a 16° AOA. The application of grooves on an aerofoil has proven to be a swift and effective technique for flow management, enhancing the performance of the aerofoil. It serves as a valuable tool for aerodynamic design and optimization, offering potential benefits such as increased lift, decreased drag, and improved stability.