Computational Study on Aerodynamic Characteristics and Behaviour of S5010 Airfoil

In this study, a numerical simulation has been conducted to understand the effect of angle of attack on the S5010 airfoil profile. ANSYS Fluent was utilized with the compliment of experimental data from literature. The 2-D computational fluid dynamic simulation were conducted to find the lift, drag and lift-to-drag ratio of S5010 airfoil at various angle of attack up till the stalling point. The k-? SST turbulent model was used to model the turbulent flow during the simulation. The data obtained was compared with available experimental data for validity and later extended to obtain stall angle of the airfoil. It was found that the stall angle of S5010 airfoil was at 11? and the maximum lift-to-drag ratio was obtained at 7.8?. Considering the simulation, acceptable solution has been achieved that can be used to compare with other airfoil profile in the future.