NACA2415 Kanat Modeli Etrafındaki Akışın DBD Plazma Girdap Üreteçleri ile Kontrolü

Bu çalışmada, girdap üreteci olarak dielektrik bariyer deşarjı plazma aktüatörlerinin NACA2415 kanat modelinin basınç katsayısı üzerine etkileri deneysel olarak düşük Reynolds sayısında incelenmiştir. Dielektrik bariyer deşarjı plazma girdap üreteçleri kanat modelinin ön kısmına (x/C=0.1) yerleştirilmiştir. Kuvvet ölçümleri altı eksenli yük hücresi kullanılarak ve basınç ölçümleri pitot statik tüpü ile yapılmıştır. Kanat modeli etrafındaki basınç dağılımları basınç transduceri ve dairesel tarama vanası kullanılarak ölçülmüştür. Deneysel sonuçlar, dielektrik bariyer deşarjı girdap üreteçleri belirli elektriksel parametrelerde sürüldüğünde kaldırma katsayısını önemli ölçüde arttırdığı ve stol açısını indirgenmiş akış etkisiyle geciktirdiğini göstermiştir. Dahası, co-rotating dielektrik bariyer deşarjı girdap üreteçlerinin sürüklemeyi katsayısını azaltmada counter-rotating dielektrik bariyer deşarjı tipine göre daha etkili olduğu gözlemlenmiştir. Ayrıca, kanat yüzeyinde üç boyutlu akış yapısı span yönünde alınan basınç ölçümleri sayesinde her iki girdap üreteci tarafından da oluşturulduğu ortaya gözlemlenmiştir. İlave olarak, her iki plazma girdap üreteçlerinin de sürükleme katsayısı üzerine etkileri stol açısında daha az iken stol öncesi ve sonrası durumlarda daha fazla olduğu gözlemlenmiştir.

Anahtar Kelimeler:

Plazma aktüatör, Kaldırma katsayısı, Sürükleme katsayısı, Girdap üreteci, Basınç katsayısı

Active Flow Control with DBD Plasma Vortex Generators around a NACA 2415 Airfoil

In this study, the effect of dielectric barrier discharge vortex generator (DBD VGs) plasma actuators on pressure coefficients of a NACA2415 airfoil are investigated experimentally at low Reynolds number. The DBD plasma VGs are placed at the leading edge of the airfoil (x/C=0.1). Force measurements with a six-axis load cell and pressure measurements with a pitot static tube are conducted. The pressure distributions over the airfoil are measured using a scan-valve unit and a pressure transducer. The experimental results showed that when the dielectric barrier discharge vortex generators were driven at a specific electrical parameter, the lift coefficient of the airfoil is increased significantly and the stall angle was postponed by induced flow effect. Moreover, the co-rotating dielectric barrier discharge vortex generators type is more effective than the counter-rotating type in reducing the drag coefficient. Furthermore, the 3D flow structure for both types of vortex generators was observed at the surface of the airfoil by using pressure measurements along with spanwise direction. In addition, it appears that the effect is less in the case of the stall angle in both plasma actuated state for drag coefficient, but they are more effective in the pre-stall angle and post-stall cases.

Keywords:

Plasma actuators, Lift coefficient, Drag coefficient, Vortex generators, pressure coefficient,

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