Multi-element Airfoil Analysis for NACA 0012 Using Computational Fluid Dynamics

In this work, a design of multi-element airfoil was studied and presented where NACA 0012 was the baseline airfoil. As a result of the pressure difference between airfoil lower and upper surfaces, the lower surface of the airfoil works as a suction wall, whereas the upper surface works as an injection wall. After creating the geometry, Ansys Fluent 19.2 software was used to conduct CFD analysis. Sparlart-Almaras turbulence model was utilized to solve RANS equations. Also, in this study, incompressible flow was assumed since the free stream velocity was at Mach 0.25. However, this research proposes a multi-element airfoil for high aerodynamic performance. Results are promising and further improvements can be made to achieve better performance.