A Study on the Plasma Actuator Electrode Geometry Configurations for Improvement of the Aerodynamic Performance of an Airfoil

Abstract

In this study, the induced flow effects of plasma generated by various types of electrode geometry configurations are presented. The model chosen for the study is a NACA0015 airfoil. The experiments are conducted in a wind tunnel at Reynolds number of 4.8×10 4. The plasma actuators mounted on the leading edge of the airfoil at chord position of 0.1 (x/C). The plasma actuators consist of an embedded and exposed electrode between which a dielectric material is placed. The applied voltage is set to 7 kV pp. The excitation frequency is also set to 3.5 kHz. Three different electrode geometry configurations, namely as linear, saw-tooth and square, are considered for the study. As a part of the experimental study, the two dimensional and three dimensional flow structures generated by the plasma actuators and related analysis results are presented. In addition, necessary measurements are also made to determine the drag and lift forces. Keywords: NACA0015 airfoil, lift and drag coefficients, square plasma actuator, sawtooth plasma actuator, linear plasma actuator Highlights • The 2D and 3D flow structure generated by the plasma actuators. • The plasma actuator geometry is determined according to the necessary conditions of the aircraft. • The stall angle is shifted by 2 degrees.

NACA 0015 Kanat Profilinin Etrafındaki Akışın Firar Kenarından Akış Emme ile Kontrol Edilmesi

“…Bunun yanı sıra, sayısal çözümlerin doğruluğunu göstermek için kontrolsüz durumda farklı hücum açılarında elde edilen CL değerleri Akbıyık vd. [15] tarafından Reynolds sayısının Re=48000 değerinde açık çevrim rüzgar tünelinde kuvvet ölçümlerinden elde edilen sonuçlar ile kıyaslanmıştır ( şekil 2b). Sayısal çözümlerden elde edilen verilerin tutunma kaybı (stol) açısına kadar (α=10°) deneysel veriler ile çok iyi örtüştüğü görülmüştür.…”

“…Akbıyık vd. [14,15] yaptıkları deneysel çalışmalar ile NACA 0015 kanat profilinin emme yüzeyine konumlandırılan DBD plazma aktüerler yardımı ile kaldırma katsayısının arttırılırken sürüklenme katsayısının azaltılabileceğini göstermişlerdir. Açıkel ve Genç [16] NACA 4412 kanat profilinde laminer ayrılma kabarcığının esnek kısmi membran ile kontrol edilmesini düşük Reynolds sayılarında çalıştırlar.…”

Experimental Study on the Snowfall Flow Control of Backward-Facing Steps Using a High-Durability Designed Plasma Electrode

“…However, the electrode configuration and shape are still being studied to improve the device's performance and expand its applications. Moreau et al [3] summarized the research conducted in the Plasma European project and introduced fine-wire electrodes, sawtooth electrodes, sliding discharge actuators using three electrodes, and a Multi-DBD PA. Akbıyık et al [4] investigated the effect on the stall angle and lift and drag coefficients for the NACA0015 wing using three types of PAs with different shapes (straight, sawtooth, and square). Asaumi et al [5] conducted a wind tunnel test with a high Reynolds number (Re = 6.0 × 10 5 ) using a tri-electrode PA composed of three electrodes for the NACA0012 blade.…”

Dynamic Instability of a Wind Turbine Blade Due to Large Deflections: An Experimental Validation

“…Additionally, researchers have used both blade element momentum (BEM) theory and actuator disk theory in the development of aeroelastic models [15] to [17]. Moreover, Akbiyik et al [18] evaluated an air foil in a wind tunnel with a test section of 570 mm × 570 mm × 1000 mm, measuring and monitoring the response signal using an oscilloscope.…”