The aim of this paper is to produce and validate a simulated model of the external flow around the NACA 2412 using ANSYS Fluent; utilising experimental data for a low velocity case (20.73 m/s) from literature. This model will be subsequently used to produce...
The NACA 2412 aerofoil with a chord length of 127 mm [24,25] was used in both the wing root and the wing tip to develop a rectangular-shaped wing of wingspan 381 mm (762/2 = 381 mm), as it is one of the wing forms that produces more lift and less drag in the subsonic flow ...