Forward-Blowing Plasma Actuation Over Forebody Asymmetric Vortex

2009 ◽  
Author(s):  
Zijie Zhao ◽  
Huaxing Li ◽  
Feng Liu ◽  
Shijun Luo
Keyword(s):  
Asymmetric Vortex ◽  
Plasma Actuation

Optimized plasma actuation on asymmetric vortex over a slender body

2018 ◽  
Vol 112 (1) ◽  
pp. 014101 ◽  
Author(s):  
Yuexiao Long ◽  
Huaxing Li ◽  
Xuanshi Meng ◽  
Haiyang Hu
Keyword(s):  
Slender Body ◽  
Asymmetric Vortex ◽  
Plasma Actuation

Effects of the Plasma Actuation on the Asymmetric Vortex around an Ogive Body at High Incidence

2012 ◽  
Author(s):  
Eunseok Lee ◽  
Jin-Ik Lee ◽  
Kwang-Seop Lee ◽  
Jurgen Seidel ◽  
Christopher Porter ◽  
...  
Keyword(s):  
Asymmetric Vortex ◽  
Plasma Actuation ◽  
High Incidence

ON THE NOx EMISSION LEVELS OF AN ASYMMETRIC VORTEX FLAME COMBUSTOR

2013 ◽  
Vol 12 (12) ◽  
pp. 2473-2478 ◽  
Author(s):  
Khalid M. Saqr ◽  
Mazlan Abdul Wahid
Keyword(s):  
Nox Emission ◽  
Asymmetric Vortex

scholarly journals Asymmetric vortex shedding in the wake of an abruptly expanding annular jet

2021 ◽  
Vol 62 (4) ◽  
Author(s):  
Maarten Vanierschot ◽  
Mustafa Percin ◽  
Bas W. van Oudheusden
Keyword(s):  
Vortex Shedding ◽  
Asymmetric Vortex ◽  
Annular Jet

Experimental investigation of the effect of active flow control on the wake of a wind turbine blade

2021 ◽  
pp. 095440622110089
Author(s):  
GholamHossein Maleki ◽  
Ali Reza Davari ◽  
Mohammad Reza Soltani
Keyword(s):  
Experimental Investigation ◽  
Wind Turbine ◽  
Turbine Blade ◽  
Active Flow Control ◽  
Leading Edge ◽  
Wind Turbine Blade ◽  
Plasma Actuators ◽  
Plasma Actuation ◽  
Surface Pressure Distribution ◽  
Stall Angle

An extensive experimental investigation was conducted to study the effects of Dielectric Barrier Discharge (DBD), on the flow field of an airfoil at low Reynolds number. The DBD was mounted near the leading edge of a section of a wind turbine blade. It is believed that DBD can postpone the separation point on the airfoil by injecting momentum to the flow. The effects of steady actuations on the velocity profiles in the wake region have been investigated. The tests were performed at α = 4 to 36 degrees i.e. from low to deep stall angles of attack regions. Both surface pressure distribution and wake profile show remarkable improvement at high angles of attack, beyond the static stall angle of the airfoil when the plasma actuation was implemented. The drag calculated from the wake momentum deficit has further shown the favorable role of the plasma actuators to control the flow over the airfoil at incidences beyond the static stall angle of attack of this airfoil. The results demonstrated that DBD has been able to postpone the stall onset significantly. It has been observed that the best performance for the plasma actuation for this airfoil is in the deep stall angles of attack range. However, below and near the static stall angles of attack, plasma augmentation was pointed out to have a negligible improvement in the aerodynamic behavior.

Tip-Disturbance Effects on Asymmetric Vortex Breakdown Around a Chined Forebody

2008 ◽  
Vol 45 (4) ◽  
pp. 1098-1104 ◽  
Author(s):  
Bao-Feng Ma ◽  
Xue-Ying Deng
Keyword(s):  
Vortex Breakdown ◽  
Asymmetric Vortex ◽  
Disturbance Effects
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