Aerodynamic performance and structural strength analysis of NACA 66-210 wing profile under different angles of attack and speed conditions

In this thesis, the aerodynamic analyses of the NACA 66-210 airfoil at speeds of 500 km/h, 600 km/h, and 700 km/h and at eight different angles between 0° and 21° were investigated. Aluminum was used as the material, drawings and modeling were created in Ansys, and transferred to Ansys Fluent and Static Structural programs for analysis. The solution was achieved using System Coupling. The analyses were conducted to determine the aerodynamic forces and moments on the object. For each angle of attack and speed, lift, drag, dynamic pressure force, coefficients, moments, deflection values, maximum, minimum, and shear stresses, as well as flow velocity distributions and pressure contours, were obtained. Future research and technological developments will have significant impacts on the NACA airfoil and other aerodynamic designs, and this work will contribute to the design of more efficient, environmentally friendly and superior air and ground vehicles in terms of performance.