Control of Boundary Layer Separation on Airfoil Using Blowing Jet and Providing Independent Regression Function for Direct Estimation of Aerodynamic Coefficients

In the present study, active flow control was performed by blowing jet at the leading edge of NACA 0015 airfoil to delay the separation of the boundary layer from the airfoil suction side. By employing 48 numerical simulations and the Response Surface Method, the relationship between the blowing jet parameters and the aerodynamic coefficients is presented as a specific regression function. The blowing width has been studied in three levels, the blowing angle and speed each in four levels. Transition SST turbulence model is used for numerical simulation and flow Reynolds number is 232940. According to the results, tangential blowing shows the most aerodynamic performance increase. This value increases from 2.56 to 42.83 inside the range under investigation for tangential blowing whereas 45° blowing jet loses its efficiency completely. Furthermore, when the blowing jet velocity rises, aerodynamic performance continuously increases. The response surface model indicates that blowing variables interactively influence the aerodynamic performance.