The document discusses using dielectric surface plasma actuators to reduce noise produced at different trailing edge designs of an airfoil. It describes an experiment where various plasma actuator configurations were 3D printed and attached to the trailing edges of a NACA 0012 airfoil, which was then tested in an anechoic chamber to analyze the reduction in broadband and tonal noise. The best performing configuration was found to be a sinusoidal plasma actuator on the serrated trailing edge, which produced the largest reductions in tonal noise.

1. Aerofoil Self Noise Reduction Using Dielectric Surface Plasma Actuators
Habiba Lais
Background: due to a predicted increase in passengers on aircrafts by 2030, this requires
more aircrafts, journeys and larger airports. This results in an increase in aviation noise.
Microphone
Aerofoil Mounted in
front of Nozzle
1m Height from
Trailing Edge
Configuration
Sin(x) Sin(x/1.5) Sin(x/3)
Results
The best configuration was the sinusoidal sin(x/1.5) on the serrated trailing edge as this had the largest
reductions of the tonal noise.
Aim: reduce broadband and tonal noise produced at different trailing edges (sharp,
serrated and blunt) of NACA 0012 airfoil using Dielectric Surface Plasma Actuators.
Method: plasma actuators are created
and buried into 3D printed trailing
edges which attach onto a NACA 0012
aerofoil.
Experimental Set-up: the aerofoil is placed in
front of an open nozzle to generate self-noise
at the trailing edge. This is placed inside an
anechoic chamber to acquire noise data using
a microphone.
Novel Plasma Actuator Designs Investigated
Serrated
Double Serrated
Downward Actuation
Sinusoidal
Alternating Sinusoidal Amplitude Spanwise