• Srinivasa Rao T

Flow control over an airfoil is very important to increase the lift to drag ratio by delaying the stall. There were many flow controlling techniques over an airfoil available in the literature. In the present study, we have made an aerodynamic modification over an airfoil called trailing edge serrations. In this study, NACA 0015 airfoil is used for conducting the wind tunnel tests. Wind tunnel tests have been conducted on NACA 0015 airfoil with and without trailing edge serrations. These tests were conducted at various test-section velocities of 15m/s, 20m/s, 25 m/s and 30 m/s for 0o, 3o, 6o, 9o, and 12o angles of attack (AoA). The tests were conducted for aerodynamic force calculations (Lift and Drag forces) and pressure distributions as well. The aerodynamics forces were measured using 3-Component External Wind Tunnel Balance. These tests were conducted in a low-speed wind tunnel.

Airfoil, Trailing edge serrations, Drag Reduction, Wind tunnel.

"AN EXPERIMENTAL STUDY ON DRAG REDUCTION OVER AN AIRFOIL", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.6, Issue 5, page no.6-9, May-2019, Available :http://www.jetir.org/papers/JETIRBT06002.pdf

"AN EXPERIMENTAL STUDY ON DRAG REDUCTION OVER AN AIRFOIL", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.6, Issue 5, page no. pp6-9, May-2019, Available at : http://www.jetir.org/papers/JETIRBT06002.pdf