Effect of Pressure Distribution of NREL S809 Airfoil with Vortex Generator

The wind tunnel experiment was carried out to investigate the effect of a vortex generator on the aerodynamics characteristics of the NREL 2809 airfoil, which was used to design the wind turbine and wings. The main objective of the research is to investigate the coefficient of pressure distributions over the NREL S809 profiled airfoil blade at a freestream velocity of 12 and 20 m/s using low-speed subsonic wind tunnel. There are two configurations of vortex generators such as the Triangular vortex generator and Rectangular vortex generator named (TVG and RVG). The vortex generator has been placed over the wing in a spanwise direction at location x/c of 0.3. The pressure distribution over the NREL S809 airfoils being investigated experimentally undergoing different conditions of operation and various AOA varies from 0° to 25° with an interval of 5°. The set of Triangular and Rectangular Vortex Generator (RVG) was arranged individually over the S809 airfoil with uniform pitch and 15° tilted with respect to streamline flow. Hence, the coefficient of pressure is estimated for both vortex generator and the result are plotted and discussed. It is found that pressure distribution is minimal at a lower angle of attack and the rectangular vortex leads to a huge variation of pressure variation compared to the Triangular vortex generator.