Dielectric Barrier Discharge Flow Control at Very Low Flight Reynolds Numbers

AIAA Journal ◽  
2008 ◽  
Vol 46 (6) ◽  
pp. 1528-1541 ◽  
Author(s):  
David Greenblatt ◽  
Berkant Goksel ◽  
Ingo Rechenberg ◽  
Chan Yong Schule ◽  
Daniel Romann ◽  
...  
Keyword(s):  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Reynolds Numbers ◽  
Dielectric Barrier ◽  
Discharge Flow

Dielectric Barrier Discharge (DBD) Plasma Actuators for Flow Control in Turbine Engines: Simulation of Flight Conditions in the Laboratory by Density Matching

2019 ◽  
Vol 36 (2) ◽  
pp. 157-173
Author(s):  
David E. Ashpis ◽  
Douglas R. Thurman
Keyword(s):  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Test Chamber ◽  
Plasma Actuators ◽  
Chamber Pressure ◽  
Turbine Engines ◽  
Dbd Plasma ◽  
Dielectric Barrier ◽  
Actuator Performance

Abstract We address requirements for laboratory testing of AC Dielectric Barrier Discharge (AC-DBD) plasma actuators for active flow control in aviation gas turbine engines. The actuator performance depends on the gas discharge properties, which, in turn, depend on the pressure and temperature. It is technically challenging to simultaneously set test-chamber pressure and temperature to the flight conditions. We propose that the AC-DBD actuator performance depends mainly on the gas density, when considering ambient conditions effects. This enables greatly simplified testing at room temperature with only chamber pressure needing to be set to match the density at flight conditions. For turbine engines, we first constructed generic models of four engine thrust-classes; 300-, 150-, 50-passenger, and military fighter, and then calculated the densities along the engine at sea-level takeoff and altitude cruise conditions. The range of chamber pressures that covers all potential applications was found to be from 3 to 1256 kPa (0.03 to 12.4 atm), depending on engine-class, flight altitude, and actuator placement in the engine. The engine models are non-proprietary and can be used as reference data for evaluation requirements of other actuator types and for other purposes. We also provided examples for air vehicles applications up to 19,812 m (65,000 ft).

Improved performance of polyimide Cirlex‐based dielectric barrier discharge plasma actuators for flow control

2021 ◽  
Author(s):  
João Nunes‐Pereira ◽  
Frederico Freire Rodrigues ◽  
Mohammadmahdi Abdollahzadehsangroudi ◽  
José Carlos Páscoa ◽  
Senentxu Lanceros‐Mendez
Keyword(s):  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Discharge Plasma ◽  
Barrier Discharge ◽  
Plasma Actuators ◽  
Dielectric Barrier Discharge Plasma ◽  
Dielectric Barrier ◽  
Barrier Discharge Plasma ◽  
Improved Performance

scholarly journals The Effect of Single Dielectric Barrier Discharge Actuators in Reducing Drag on an Ahmed Body

Fluids ◽  
2020 ◽  
Vol 5 (4) ◽  
pp. 244
Author(s):  
Saber Karimi ◽  
Arash Zargar ◽  
Mahmoud Mani ◽  
Arman Hemmati
Keyword(s):  
Drag Reduction ◽  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Three Dimensional ◽  
Reynolds Numbers ◽  
Aerodynamic Performance ◽  
Dielectric Barrier ◽  
Car Model ◽  
Slant Surface ◽  
Ahmed Body

The feasibility of a single dielectric barrier discharge (SDBD) actuator in controlling flow over an Ahmed body, representing a simplified car model, has been numerically and experimentally investigated at Reynolds numbers of 7.68×105 and 2.25×105. The Ahmed body had slant angles of 25∘ and 35∘. The results showed that SDBD actuators could significantly enhance the aerodynamic performance of the Ahmed body. Several arrangements of the actuators on the slant surface and the rear face of the model were examined to identify the most effective arrangement for drag reduction. This arrangement resulted in an approximately 6.1% drag reduction. This improvement in aerodynamic performance is attributed to the alteration of three-dimensional wake structures due to the presence of SDBD, which coincides with surface pressure variations on the slant and rear faces of the Ahmed body.

scholarly journals Coherent structures induced by dielectric barrier discharge plasma actuator

2017 ◽  
Vol 31 (32) ◽  
pp. 1850038 ◽  
Author(s):  
Xin Zhang ◽  
Huaxing Li ◽  
Kwing So Choi ◽  
Longfei Song
Keyword(s):  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Coherent Structures ◽  
High Speed ◽  
Barrier Discharge ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Peak Voltage ◽  
Dielectric Barrier ◽  
Piv Measurement

The structures of a flow field induced by a plasma actuator were investigated experimentally in quiescent air using high-speed Particle Image Velocimetry (PIV) technology. The motivation behind was to figure out the flow control mechanism of the plasma technique. A symmetrical Dielectric Barrier Discharge (DBD) plasma actuator was mounted on the suction side of the SC (2)-0714 supercritical airfoil. The results demonstrated that the plasma jet had some coherent structures in the separated shear layer and these structures were linked to a dominant frequency of [Formula: see text] = 39 Hz when the peak-to-peak voltage of plasma actuator was 9.8 kV. The high speed PIV measurement of the induced airflow suggested that the plasma actuator could excite the flow instabilities which lead to production of the roll-up vortex. Analysis of transient results indicated that the roll-up vortices had the process of formation, movement, merging and breakdown. This could promote the entrainment effect of plasma actuator between the outside airflow and boundary layer flow, which is very important for flow control applications.

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