• AYESHA KHAN M
• SANDEEEPA T S

The current study investigates the numerical simulations of symmetrical infinite wing of NACA 0012 with modified trailing edges. The trailing edge serrations have been provided to study the aerodynamic performances. The objective is to understand the effects of changes in aerodynamic coefficients with the saw tooth trailing edge serrations. The detailed mathematical investigations have been carried out using CFD technique for various angles of attack (0o to 20o). Spalart-Allmaras turbulence model with standard wall function is considered to solve the turbulent parameters. Current study has been focused on visualising the changes in flow behaviour and vortex mechanism at various Reynolds numbers (30 m/s, 93.7 m/s) and modified NACA wings and also computing the performance characteristics numerically and observing the changes in performance characteristics with the base wing. The application of serrations to the trailing edge results in control of vortex shedding and changes in performance characteristics of the modified wing.

"INVESTIGATION ON AERODYNAMIC PERFORMANCE OF SYMMETRIC WINGS WITH SERRATIONS ", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.6, Issue 6, page no.540-546, June 2019, Available :http://www.jetir.org/papers/JETIR1906V76.pdf

"INVESTIGATION ON AERODYNAMIC PERFORMANCE OF SYMMETRIC WINGS WITH SERRATIONS ", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.6, Issue 6, page no. pp540-546, June 2019, Available at : http://www.jetir.org/papers/JETIR1906V76.pdf