Boundary Layer Control with a Plasma Actuator Utilizing a Large GND Mesh Electrode and Two HV Electrode...

Area of Science:

• Aerospace Engineering
• Fluid Dynamics
• Plasma Physics

Background:

• Plasma actuators are used to control airflow over surfaces.
• Traditional electrode geometries have limitations in performance enhancement.
• Novel electrode designs are needed to improve aerodynamic efficiency.

Purpose of the Study:

• To investigate the effect of different high-voltage electrode geometries on plasma actuator performance.
• To evaluate the impact of these actuators on boundary layer flow and lift coefficient.
• To introduce a new plasma actuator design with mesh electrodes.

Main Methods:

• Experimental studies using a wind tunnel.
• Testing a wing model (SD 7003 profile) with a custom-designed Dielectric Barrier Discharge (DBD) plasma actuator.
• Varying high-voltage electrode configurations (solid copper vs. mesh) and operating conditions (voltage, airflow velocity, angle of attack).
• Measurements of lift coefficient (C_L) across a range of Reynolds numbers (Re = 87,985–351,939).

Main Results:

• A plasma actuator with a mesh high-voltage electrode and large mesh ground electrode demonstrated a notable increase in lift coefficient.
• This improvement was observed at an angle of attack of 5 degrees and airflow velocities from 5 m/s to 20 m/s.
• Solid copper high-voltage electrodes showed negligible impact on the lift coefficient, whether the actuator was on or off.

Conclusions:

• The use of a mesh high-voltage electrode in a plasma actuator represents a significant advancement in aerodynamic control.
• This novel design offers a promising method for enhancing lift and potentially improving aircraft wing performance.
• Further research into mesh electrode configurations could lead to more efficient aerodynamic solutions.