Enhancing aerodynamic performance of a two-dimensional airfoil using plasma actuators

• Published in: Aerospace science and technology 2025-03, Vol.158, p.109882, Article 109882
• Main Authors: ÜNAL, Nesij, ÖZ, Yahya, ÜNAL, Elif Albina, OKTAY, Tuğrul
• Format: Article
• Language: English
• Subjects: Active flow control; Aerodynamic performance enhancement; Experimental and computational flow analyses; Flow separation control; Machine learning in aerodynamics; Plasma actuators; Surface dielectric barrier discharge
• ISSN: 1270-9638
• DOI: 10.1016/j.ast.2024.109882

•Plasma actuators improved the lift-to-drag ratio by up to 161% at optimal conditions.•A novel actuator placement strategy enhanced aerodynamic performance of airfoils.•ANFIS models predicted lift and drag trends reducing reliance on wind tunnel tests.•Experimental and CFD analyses validated plasma's effectiveness in flow separation control.•Machine learning with experimental flow control techniques was integrated. Active and passive flow control methods are used nowadays to increase aerodynamic performance of aircraft. In passive flow control methods, performance improvement is realized without using external energy while for active flow control motion around the object is managed by using energy in the system without any change in body structure. Some passive flow control methods used today include placing a separator plate on the back of the object, surface roughness or flow disrupting wire-like elements placed on the surface, roundings at sharp corners, notches-slits opened to certain parts of the object and controlling flow with a control rod placed in front of the object. Methods used in active flow control are deforming surfaces, zero net mass flux actuators, non-zero net mass flux actuators, moving object / surface actuators, flexible as well as displacement blades and plasma assisted actuators. In recent years, hybrid control methods also have been developed by combining both active and passive control methods. In this manuscript a study was carried out on plasma actuators which are classified as active flow control. Scope of the study includes selection of plasma and airfoil type, designing and producing a novel wing, experimental and computational studies for defining flow separation points of the wing, plasma actuator placement on the wing, performing wind tunnel tests and evaluating test results using artificial neural networks. Thus, this study investigates use of plasma actuators to enhance aerodynamic performance of an airfoil, i.e. optimizing the lift-to-drag ratio for enhanced range as well as endurance and increasing the maximum lift coefficient to enable potential reductions in wing area, integrating experimental, computational and machine learning approaches to provide a comprehensive analysis. A novel actuator placement strategy was developed based on flow visualization and simulations ensuring targeted flow control at critical regions of the airfoil. As a result, variations in the lift coefficient CL, drag coefficient CD and lift-to-