Investigation of the flow around an aircraft wing of section NACA 2412 utilising ANSYS fluent

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 data for a high velocity case (272.1 m/s, Mach = 0.8) which is the practical velocity for commercial aircraft. Both an infinite aspect ratio wing (2D) and a finite aspect ratio wing (3D) will be the subjects of this investigation. Experimental data on which the simulated models will be compared and hence validated is taken from Jacobs et al. [1]. This experimental data contains both a finite aspect ratio wing and an infinite aspect ratio wing. An accurate simulation model of the external flow around a wing will be beneficial in the visualisation of the flow; particularly in the investigation of the onset of a stall and the aerodynamic characteristic differences between the wing root and wing tip. The model will also provide simulated data of an external flow condition of which no experimental data currently exists. Finally, value will be gained in the investigation between the differences of an external flow around a 2-dimensional (2D) wing versus a 3-dimensional (3D) wing. All simulations exhibited flow physics consistent with those seen in experimental data; further validating the results. A detailed methodology has been provided with a view that new data becomes available for this aerofoil and wing geometry. Considering the aerofoil simulation, incredible accuracy has been achieved. However, with regards to the wing simulation, further work is required to identify the issue which resulted in a lower lift curve slope when compared to the experimental data