摘要: The effects of an unsteady fluidic boundary layer fence are experimentally investigated on a 30-degree swept NACA 643-618 wing with semi-span aspect ratio of 2.2. Two methods of unsteady fluidic actuators are explored: pulsed vort... 展开 The effects of an unsteady fluidic boundary layer fence are experimentally investigated on a 30-degree swept NACA 643-618 wing with semi-span aspect ratio of 2.2. Two methods of unsteady fluidic actuators are explored: pulsed vortex generating jets and fluidic oscillators. Both methods consist of a streamwise row of actuators located at 70% span on the suction surface. Injected air is either pulsed with a solenoid valve at varying frequencies and duty cycles or naturally sweeps with oscillation frequencies proportional to the mass flow rate. Load cell measurements are performed at Re= 100,000 to understand the magnitude of performance benefits of each technique. The Cl enhancements are directly related to the time-average blowing ratio of the actuation technique, and pre-baseline stall performance can be predicted by strictly knowing the duty cycle and blowing ratio of the jets. An optimal pulsing frequency was determined between SO and 100 Hz which improved the lift similar to steady actuators with the same blowing ratio. The impacts of duty cycle and blowing ratio are explored, and a comparison between maximum lift increase and momentum coefficient found diminishing returns past C_μ=1.5%. 收起