Investigation of Active Flow Control over NACA0015 Airfoil Via Blowing

Abstract

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 airfo il's upper surface under Re=455000 in 6 different angles of attack 12 o to 17 o is investigated. More than 200 nu merical simulat ions are conducted over a range of parameters of jet locations (10%, 30% and 50% of chord fro m leading edge), jet velocity ratios (1, 2 and 6 time of free stream velocity) and jet angles (0 o , 30 o and 45 o relative 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. Simulat ion 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 airfo il.