scholarly journals Adaptive Flow Control of Low Reynolds Number Aerodynamics Using a Dielectric Barrier Discharge Actuator

2009 ◽  
Author(s):  
Young-Chang Cho ◽  
Matthew Fledderjohn ◽  
Matthew Holzel ◽  
Balaji Jayaraman ◽  
Mario Santillo ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Low Reynolds Number ◽  
Dielectric Barrier ◽  
Adaptive Flow Control ◽  
Low Reynolds

Simulation of dielectric barrier discharge actuator at low Reynolds number

2020 ◽  
Vol 92 (4) ◽  
pp. 571-578
Author(s):  
Nima Vaziri ◽  
Ming-Jyh Chern ◽  
Tzyy-Leng Horng ◽  
Syamsuri Syamsuri
Keyword(s):  
Reynolds Number ◽  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Low Reynolds Number ◽  
Lift Coefficient ◽  
Immersed Boundary ◽  
Ray Casting ◽  
Dielectric Barrier ◽  
Content Type ◽  
Low Reynolds

Purpose The purpose of this study is to the modeling of the dielectric barrier discharge (DBD) actuator on the Eppler 387 (E387) airfoil in low Reynolds number conditions. Design/methodology/approach A validated direct-forcing immersed boundary method is used to solve the governing equations. A linear electric field model is used to simulate the DBD actuator. A ray-casting technique is used to define the geometry. Findings The purposed model is validated against the former studies. Next, the drag and lift coefficients in the static stall of the E387 airfoil are investigated. Results show that when the DBD actuator is on, both of the coefficients are increased. The effects of the location, applied voltage and applied frequency are also studied and find that the leading-edge actuator with higher voltage and frequency has better improvement in the forces. Finally, the dynamic stall of the E387 with the DBD actuator is considered. The simulation shows that generally when the DBD is on, the lift coefficient in the pitch-up section has lower values and in the pitch-down has higher values than the DBD off mode. Practical implications It is demonstrated that using the DBD actuator on E387 in the low Reynolds number condition can increase the lift and drag forces. Therefore, the application of the airfoil must be considered. Originality/value The results show that sometimes the DBD actuator has different effects on E387 airfoil in low Reynolds number mode than the general understanding of this tool.

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).

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