Comparison of the Linear and Spanwise-Segmented DBD Plasma Actuators on Flow Control Around a NACA0015 Airfoil
Küçük Resim Yok
Tarih
2017
Dergi Başlığı
Dergi ISSN
Cilt Başlığı
Yayıncı
IEEE-Inst Electrical Electronics Engineers Inc
Erişim Hakkı
info:eu-repo/semantics/closedAccess
Özet
In this paper, linear and spanwise-segmented plasma actuator implementations as well as base airfoil with no plasma cases are presented. These approaches are used to control the flow around a NACA0015 airfoil. The experiments were conducted in a wind tunnel at Reynolds number of 3.6x10(4). The plasma actuators mounted on the leading edge of the airfoil at chord position of 0.1 (x/C). The electrical parameters used for the plasma generating device are set to constant values of 6-kV(pp) applied voltage and 3.5-kHz excitation frequency. It is observed that the use of spanwise-segmented plasma actuators converts the 2-D flow structure around the airfoil into 3-D forcing flow structure. The change of the wake region width of the airfoil is visualized by using the smoke-wire method. The flow visualization is performed at attack angles of 0 degrees, 5 degrees, 10 degrees, and 15 degrees. In addition, necessary measurements are also made to determine drag and lift forces. A comparative study on the drag and lift forces for the NACA0015 airfoil is performed. As a part of the conclusions, linear and spanwise-segmented plasma actuator implementations as well as base airfoil with no plasma cases are compared and related results on flow control are presented.
Açıklama
Anahtar Kelimeler
Actuators, aircraft, flow control, force measurement, plasma applications
Kaynak
Ieee Transactions on Plasma Science
WoS Q Değeri
Q3
Scopus Q Değeri
Q3
Cilt
45
Sayı
11
