Computation of flow around a naca 0015 aerofoil with znmf jet control: Potential savings of an unstructured mesh?

Abstract

The flow around a NACA 0015 aerofoil with a zero-net-mass-flux jets (ZNMF) located at the leading edge of the aerofoil is simulated using Large Eddy Simulation (LES). An incidence angle of 18◦ is used such that without flow control, the flow exhibits laminar separation from the tip of the aerofoil and an associated loss of lift. The oscillating ZNMF jet is designed to introduce small scale structures into the boundary layer at the mouth of the jet to breakup the larger, more stable low speed structures. These long thin structures are perturbed to the point that they become unstable and turbulent flow ensues, where higher momentum enables the flow to maintain attachment around the tip and suc..