Investigation of Active Flow Control over NACA0015 Airfoil Via Blowing

In this study the concept of Active flow control using a blowing jet with a width of 2.5% of chord length which places on NACA0015 airfoil's upper surface under Re=455000 in 6 different angles of attack 12o to 17o is investigated. More than 200 numerical simulations are conducted over a range of parameters of jet locations (10%, 30% and 50% of chord from leading edge), jet velocity ratios (1, 2 and 6 time of free stream velocity) and jet angles (0o, 30o and 45orelative to the airfoil surface) are investigated. The viscous model used for modeling the turbulence is Spalart-Allmaras and a commercial CFD code, the FLUENT, is used to solve flow equations. Simulation results show that the blowing will increase the amount of lift and reduce drag. Also at high angles of attack, the blowing delay separation and improve the performance of the airfoil.