Author

Marco Sansone

Date of Award

12-2015

Document Type

Thesis - Open Access

Degree Name

Master of Science in Aerospace Engineering

Department

Graduate Studies

Committee Chair

Dr. Vladimir Golubev

First Committee Member

Dr. Reda Mankbadi

Second Committee Member

Dr. Crystal Pasiliao

Abstract

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.

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