Three-dimensional numerical study of the effect of blowing angle on the aerodynamic characteristics of a wing section with NACA 0012 airfoil

In this study, the effect of blowing angle on coefficients of aerodynamic of NACA0012 airfoil at Re=4×106 has been investigated. In the present research, the effect of three-dimensional blowing jet on the aerodynamic performance of the wing has been considered. The changes of lift and drag coefficients were studied by using the blowing near the leading edge of the airfoil for angles of attack of 12, 14, 16, 18 and 20 degrees. Due to the application of blowing through circular holes, a three-dimensional solution was used for the purpose of analysis and study, which will be computationally expensive. The analysis carried out in this case was performed with the assumption of incompressible and steady flow around a three-dimensional wing section in Fluent software. The results showed that the blowing has a negligible effect on the lift and drag coefficients at angles of attack less than 14 degrees. It is for this reason that only the effects of the blowing at high angles of attack are considered. The greatest increase in the lift coefficient and the greatest decrease in the drag coefficient occurs at the angle of attack of 16 degrees, which is the stall angle. The results showed that as the jet angle increases, the aerodynamic performance decreases.