Computational fluid dynamic analysis of stall number under synthetic jet impact: NACA GA(W)-2 airfoil

This study presents a numerical investigation into active flow control (AFC) on a NACA GA(W)-2 airfoil using synthetic jet actuators (SJAs) to enhance lift and delay stall, focusing specifically on the novel application of dual SJAs on the airfoil’s suction surface, an area previously unexplored for this airfoil type. Computational fluid dynamics(CFD) simulations, validated against experimental data, were employed. Initially, optimal locations for a single SJA were identified, with 12% chord (C) from the leading edge yielding the maximum lift improvement (10.4%) and 25% C providing the greatest drag reduction ([Formula: see text]5%). Building on these findings, the core contribution investigates the aerodynamic effects of a dual SJA configuration, placing jets simultaneously at the 12% C and 25% C locations. This dual setup was analyzed at post-stall angles of attack (16[Formula: see text] and 22[Formula: see text]). Results indicate that at 16[Formula: see text] AOA, the dual SJA configuration offered better drag reduction than the single SJA at 12% C. At 22[Formula: see text] AOA, the dual SJA significantly reduced drag compared to both single SJA cases (30.85% reduction vs 12% C SJA; 3.25% reduction vs 25% C SJA), although lift improvement was only seen relative to the single 25% C SJA case.