THE EFFECT OF THE SPLIT NACA 0015 AIRFOIL ON VARIATIONS IN REYNOLDS NUMBER

Abstract

This research will discuss the advantages of a NACA 0015 airfoil with a split configuration under varying Reynolds numbers. Computational Fluid Dynamics (CFD) simulations with a K-epsilon turbulence model were conducted on a two-dimensional split airfoil to achieve this goal. Initially, simulations were carried out for the unsplit airfoil geometry at different Reynolds numbers within an angle of attack (AoA) range of 0⁰ to 25⁰. Subsequently, simulations were performed for the split airfoil geometry at various Reynolds numbers within the same AoA range. The unsplit airfoil experiences stall at AoA greater than 11⁰ degrees, while the split airfoil experiences stall at AoA greater than 13⁰ degrees. Additionally, using a split airfoil enhances C_l, with an average increase of approximately 7-8% across different Reynolds numbers. In addition to the C_l improvement, the split airfoil exhibits lower C_d values than the unsplit airfoil, with an average reduction of about 26-28% across all Reynolds number variations. Overall, using separate airfoils improves the aerodynamic performance of the airfoil, with an average increase in C_l/C_d of approximately 33-37% across all Reynolds number variations. In conclusion, the split airfoil performs better than the unsplit airfoil.