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The article presents the results of experimental
studies on the influence of the geometry of high-voltage plasma
actuator electrodes on the change of flow in the boundary layer
and their influence on the change of the lift coefficient. The
plasma actuator used in the described experimental studies has
a completely different structure. The experimental model of
the plasma actuator uses a large mesh ground electrode and
different geometries of the high voltage electrodes, copper solid
electrodes and mesh electrode, (the use of mesh electrodes,
large GND and HV is a new solution). The plasma actuator
was placed directly on the surface of the wing model with the
SD 7003 profile. The wing model with the plasma actuator was
placed in the wind tunnel. All experimental tests carried out
were carried out for various configurations of the angle of
attack in the range α = 5 - 20 degrees for four air velocities in
the range V = 5 - 20 m/s. The DBD plasma actuator is powered
by a high voltage power supply with a voltage range from Vp =
7.5 – 15 kV. The use of a high-voltage mesh electrode allowed
for an increase in the lift coefficient (CL) for the angle of attack
α = 5 degrees and the air flow velocity in the range from V =
5 m/s to 20 m/s, while the use of copper electrodes HV with the
plasma actuator turned off and on, are very small (close to
zero).
