Fuel consumption and the reduction of emissions are of considerable importance in the design of aircrafts. Consequently, a substantial number of studies have been conducted in the extant literature to enhance the effectiveness of wings. In recent decades, boundary layer control methods have assumed a prominent role in achieving these objectives. The primary function of these methods is to delay the onset of flow separation, thereby reducing drag force and enhancing overall effectiveness. These methods can be categorised into two distinct groups: passive and active boundary layer control methods. Passive methods include riblets and vortex generators. Conversely, active methods encompass blowing, suction and zero net mass flux techniques. The present study employs a loudspeaker-driven synthetic jet actuator (SJA), a zero net mass flux method, to simulate the effects of geometrically optimised SJA at different working conditions (e.g. variable frequencies, amplitudes, etc.). The conditions under which these simulations are conducted are determined by Computational Fluid Dynamics (CFD). Unsteady Reynolds-averaged Navier-Stokes (URANS) simulations are conducted using the RNG k-ε turbulence model. Visual investigations of unsteady synthetic jets formed by the SJA are performed at frequencies ranging from 50 Hz to 130 Hz.