An Experimental Investigation on the Thermal Effects of NS-DBD and AC-DBD Plasma Actuators for Aircraft Icing Mitigation

2018 ◽  
Author(s):  
Cem Kolbakir ◽  
Yang Liu ◽  
Hui Hu ◽  
Andrey Starikovskiy ◽  
Richard B. Miles
Keyword(s):  
Experimental Investigation ◽  
Thermal Effects ◽  
Plasma Actuators ◽  
Aircraft Icing ◽  
Dbd Plasma

Experimental investigation of DBD plasma actuators on a BWB aerial vehicle model

2018 ◽  
Author(s):  
Pavlos Kaparos ◽  
Savvas Koltsakidis ◽  
Pericles Panagiotou ◽  
Kyros Yakinthos
Keyword(s):  
Experimental Investigation ◽  
Plasma Actuators ◽  
Vehicle Model ◽  
Dbd Plasma ◽  
Aerial Vehicle

Experimental investigation of lift enhancement for flying wing aircraft using nanosecond DBD plasma actuators

2017 ◽  
Vol 19 (4) ◽  
pp. 044002 ◽  
Author(s):  
Junkai YAO ◽  
Danjie ZHOU ◽  
Haibo HE ◽  
Chengjun HE ◽  
Zhiwei SHI ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Plasma Actuators ◽  
Dbd Plasma ◽  
Lift Enhancement

Experimental Investigation on Improving the Aerodynamic Performance of Swept Aircraft by DBD Plasma

2011 ◽  
Vol 110-116 ◽  
pp. 3234-3242
Author(s):  
Wei He ◽  
Zhong Guo Niu ◽  
Bo Pan ◽  
Qi Lin
Keyword(s):  
Experimental Investigation ◽  
Aerodynamic Performance ◽  
Plasma Actuators ◽  
Dielectric Barrier Discharges ◽  
Dbd Plasma ◽  
Induced Flow ◽  
Lift And Drag ◽  
Particle Imaging ◽  
Barrier Discharges ◽  
Drag Ratio

The experimental investigation on improving the aircraft aerodynamic performance by DBD (Dielectric Barrier Discharges) plasma is described in this paper. The test has been carried out in a low speed wind tunnel with a wept aircraft model. The plasma actuators were set on the upper surface of swept wing combining with airplane body model. The test results presented include the flow field visualization by PIV (Particle Imaging Velocimetry), lift and drag characteristics under the plasma actuators off and on. The results show that the induced flow by DBD plasma may control the separation on the upper surface of the wing evidently, so that the highest stalling angle of the model increases and maximum lift-to-drag ratio rises, respectively. But with the wind velocity increasing, the effect of the plasma decreases gradually.

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.

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