Aerodynamic and acoustic behavior of a finite span wing equipped with synthetic jet actuator

In the current paper, aerodynamic and acoustic behaviors of a finite span wing with a synthetic jet actuator (SJA) are investigated using the DES turbulence model at three different angles of attack (AOA=14°, 18° and 25°). Aerodynamically, the main role of the SJA actuator is causing the vortex breakdown, weakening the separation effects and generating aerodynamic forces which fluctuate in time. As the AOA increases, the separated area becomes larger and stronger and, hence, the lift and drag values turns from the harmonic shapes to irregular fluctuation. From the acoustic point of view, for the AOAs of 14° and 18° the sound source occurs near the trailing edge. However, at AOA=25°, the dominant frequency of sound spectrum tends to move to a low frequency and the overall sound pressure level becomes the highest. Also, for this AOA the sound emits from both trailing edge and leading edge. Moreover, it is observed that the sound directivity changes to a no-dipole shape at a frequency lower than that of AOA=14° and 18°.