Abstract
Numerical investigation was made to study the aerodynamic characteristics of the Tubercle NACA2412 airfoil is used in the design of aircraft wing and wind turbine blades. In this paper, computational study aimed to observe the aerodynamic characteristics of 3D airfoil NACA 2412 with peak and trough chord length as 100 mm and 80 mm respectively. The co-efficient of pressure performance of NACA2412 airfoil with tubercle leading edge profile blade used to investigate numerically for enhance the aerodynamics performance of Wind turbine. Investigation were made to find pressure distribution over the Tubercle airfoils under various freestream velocity conditions such as 5 m/s, 10 m/s, 15 m/s and 20 m/s with different angle of attacks from −30° to 30° with the step of 5°. The Spalart–Allmaras turbulent model was used to carry out simulations in the ANSYS Fluent software. Therefore, the Coefficient of pressure distribution is calculated at peak and trough of the tubercle airfoil at different operating conditions and results are plotted in the graph. It is observed that pressure distribution varies drastically near the leading edge for all velocities. Analysis for different velocities with a wide range of angle of attacks are discussed and presented with relevant details.
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