INVESTIGATING THE EFFECTS OF PLASMA ACTUATOR ON THE FLOW CONTROL AROUND NACA2415 AIRFOIL
Küçük Resim Yok
Tarih
2020
Yazarlar
Dergi Başlığı
Dergi ISSN
Cilt Başlığı
Yayıncı
Turkish Soc Thermal Sciences Technology
Erişim Hakkı
info:eu-repo/semantics/closedAccess
Özet
In this study, the effects of the plasma actuator on flow control at varied Reynolds numbers and attack angles are examined. Plasma actuator is placed on the NACA2415 airfoil at x/C = 0.1. The effect of the actuator to active flow control is examined at Reynolds number between 8x10(3) and 9x10(4) in the wind tunnel. The lift force which acted on the airfoil was measured by using a force balance system. The velocity measurements were done by the hot-wire probe, located at the wake region, and the flow around model was visualized by the smoke wire method. When the plasma was active, an increased lift force and a narrowed wake region are observed. The stall angle shifted to the higher attack angle by the effective active flow control at low Reynolds numbers. Prevent of the flow separation was enhanced up to 18 degrees angle of attack and the maximum lift force occurred at the 14 degrees angle of attack which is doubled when the plasma actuator is on.
Açıklama
Anahtar Kelimeler
airfoil, flow control, lift force, plasma actuator
Kaynak
Isi Bilimi Ve Teknigi Dergisi-Journal of Thermal Science and Technology
WoS Q Değeri
Q4
Scopus Q Değeri
Q4
Cilt
40
Sayı
1
