Numerical Study of Synthetic-Jet Actuation Effect on Airfoil Trailing Edge Noise

<p>The current study conducts numerical simulations to assess the possibility of employing Synthetic Jet Actuators (SJAs) as active noise control devices for reduction of airfoil acoustic radiation. High-accuracy numerical efforts employ a sixth-order accurate Navier-Strokes solver implementing a low-pass filtering of poorly resolved high-frequency solution content to retain numerical accuracy and stability over the range of transitional flow regimes. In the adopted numerical procedure, the actuator is modeled without its resonator cavity through imposing a simple fluctuating-velocity boundary condition at the bottom orifice of the actuator. The orifice cavity with the properly defined boundary condition is embedded into the airfoil surface for conducting high-accuracy viscous analysis of SJA-based active noise control. The effects of SJA location and actuation frequency on airfoil sound radiation are examined for uniform upstream flow conditions.</p>

Name thesis:degree_name

Master of Science in Aerospace Engineering

Level thesis:degree_level

Thesis - Open Access

Discipline thesis:degree_discipline

Aerospace Engineering

Year

2015

Author dc:creator

• Sansone, Marco

• synthetic jet actuators
• airfoils
• trailing edge
• noise
• Aerodynamics and Fluid Mechanics
• Aerospace Engineering

Repository record dc:identifier

https://commons.erau.edu/edt/243

OAI identifier oai:identifier

oai:commons.erau.edu:edt-1242