MOMENTUM COEFFICIENT EFFECTS ON THE AERODYNAMIC CHARACTERISTICS OF AN AIRFOIL OF SYNTHETIC JET ACTUATOR

摘要

Active flow control using perpendicular synthetic jet actuator on NACA0015 airfoil is experimented in the wind tunnel at a chord Reynolds number of 3.02 × 10~5 and at zero angle of attack. Upon actuation of the synthetic jet actuator, pressure distribution of the airfoil is introduced to the leading edge's spike, trailing edge's spike, suction peak, and pressure recovery which are found to substantially alter the aerodynamic forces. In this paper, the investigations on the effects of these four occurrences towards aerodynamic forces and their developments in physical characteristics at ranges of actuation frequency (F~+ = 11-21.5) and momentum coefficient (C_μ = 4.18 × 10~(-5)-8.00 × 10~(-3)) are presented.