Numerical Analysis of Flow Separation Control of an Airfoil by Plasma Actuator
DOI:
https://doi.org/10.38032/scse.2025.3.165Keywords:
Plasma Actuator, Shyy Model, Airfoil, Flow ControlAbstract
Plasma actuators operating under atmospheric conditions show great promise for flow control due to their unique physical characteristics, such as the body force generated by a strong electric field. This study numerically examines the effect of low-powered plasma actuation on the aerodynamic performance of a NACA 2412 airfoil. Utilizing the Shyy plasma actuation model, the study simulates its effects through defined functions. The analysis investigates the lift and drag coefficients at various angles of attack, with a freestream velocity of 14.5 m/s. Without plasma actuation, the airfoil experiences common aerodynamic challenges, such as flow separation near the trailing edge, which reduces efficiency. However, plasma actuation accelerates the airflow over the upper surface, delaying flow separation and decreasing drag. This results in smoother airflow and increased lift, particularly at higher angles of attack. The use of plasma actuation achieved approximately a 21% increase in the lift coefficient. Overall, plasma actuators enhance airflow control, reduce drag, and boost lift, improving the airfoil’s aerodynamic performance. This improvement is supported by pressure contour analysis, which demonstrates a more favorable pressure distribution with plasma actuation.
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Copyright (c) 2025 Jishan Ahmed , Aditya Das, Mushfiqur Rahman Shihab, Mohammad Ilias Inam (Author)
This work is licensed under a Creative Commons Attribution 4.0 International License.
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