Analytical Modelling of Plasma Actuator-Induced Flow Control on a NACA 0015 Aerofoil

Abstract

Plasma actuators function as quick, lightweight solutions for aerofoil airflow control through non-moving parts. The majority of Dielectric Barrier Discharge (DBD) actuator research relies on Computational Fluid Dynamics (CFD), but this paper demonstrates an analytical solution through MATLAB-based modelling. The use of a Gaussian plasma body force distribution relies on the voltage, frequency, and shape of the actuator to predict its effects on airflow using thin-aerofoil theory. The model shows that lift coefficient changes based on actuator placement and strength can produce lift increases of up to 15% during stall conditions. The analytical results match experimental data from published research regarding lift improvement and the best actuator placement positions.

Introduction

Effective airflow control is crucial for aerofoil performance, enhancing lift, reducing drag, and improving stall behavior to increase safety and efficiency. Flow control methods are divided into passive (using vortex generators and fixed devices) and active (using external energy like suction or plasma actuators). Active control delays flow separation, maintaining lift at higher angles of attack and reducing noise by altering turbulent structures.

The Reynolds number influences flow stability; at moderate values, boundary layer separation can increase drag and reduce lift. Plasma actuators, especially Dielectric Barrier Discharge (DBD) types, manipulate airflow by generating ionic wind using electric fields without moving parts, making them compact, fast-responding, and reliable for aerodynamic applications.

DBD plasma actuators produce body forces through electrostatic and momentum-transfer mechanisms, accelerating air near the aerofoil surface to control flow. Modelling these forces is complex, so simplified empirical models like the Suzen-Huang Gaussian profile are used for practical aerodynamic predictions.

Lift enhancement from plasma actuators can be analyzed by integrating body force effects into classical thin-airfoil theory. This hybrid semi-analytical method estimates increased circulation and lift coefficient without intensive CFD simulations, enabling quick assessments of actuator effects. However, it assumes inviscid, incompressible flow at small angles of attack and does not directly model turbulence or stall.

A MATLAB implementation approximates plasma actuator body force and predicts a lift coefficient increase, demonstrating the feasibility of plasma flow control for aerofoil performance improvement.

Conclusion

Fundamentally, the aerodynamic impact of DBD plasma actuators on a NACA 0015 aerofoil has been analysed using a MATLAB-based Gaussian body force model. On the whole, lift can be significantly enhanced by increasing the actuator’s special spread and placing it near the leading edge, producing an increase in lift coefficient of up to 15%. Plasma actuator technology is still being developed, but it offers potential to be integrated into UAV and morphing-wing aircraft technologies by using more advanced modelling techniques such as feedback-controlled actuation and high-fidelity computational fluid dynamics.

Copyright

Copyright © 2025 Ilia Yusefi-Dehlaghi. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.