Three-dimensional patterns in dielectric barrier discharge with “H” shaped gas gap

2016 ◽  
Vol 23 (8) ◽  
pp. 083526 ◽  
Author(s):  
Xing Gao ◽  
Lifang Dong ◽  
Hao Wang ◽  
Hao Zhang ◽  
Ying Liu ◽  
...  
Keyword(s):  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Three Dimensional ◽  
Dielectric Barrier ◽  
Gas Gap

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 Transition control in a three-dimensional boundary layer at elevated free stream turbulence using dielectric barrier discharge

2019 ◽  
Vol 486 (6) ◽  
pp. 668-672
Author(s):  
S. A. Baranov ◽  
A. Ph. Kiselev ◽  
I. A. Moralev ◽  
D. S. Sboev ◽  
S. N. Tolkachev ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Dielectric Barrier Discharge ◽  
Free Stream ◽  
Barrier Discharge ◽  
Flow Instability ◽  
Three Dimensional ◽  
Cross Flow ◽  
Dielectric Barrier ◽  
Free Stream Turbulence ◽  
Dimensional Boundary

The results of an experimental study of the effect of dielectric barrier discharge (DBR) actuator on laminar-turbulent transition in a three-dimensional boundary layer under influence of elevated free-stream turbulence are presented. The travelling cross-flow instability modes are dominated in transition in a base configuration. Their characteristics do not depend on a spanwise position. The DBD-actuator that generated stationary cross-flow vortices with the predefined spanwise wavelength when turned on was capable to reduce a turbulent spots production rate in comparison to the base regime.

Formation mechanism and application of a three-dimensional pattern in dielectric barrier discharge system

2020 ◽  
Vol 27 (5) ◽  
pp. 053503
Author(s):  
Guanglin Yu ◽  
Lifang Dong ◽  
Liting Guo ◽  
Fucheng Liu ◽  
Caixia Li ◽  
...  
Keyword(s):  
Dielectric Barrier Discharge ◽  
Formation Mechanism ◽  
Barrier Discharge ◽  
Three Dimensional ◽  
Discharge System ◽  
Dielectric Barrier

Monitoring of a dielectric barrier discharge-based process using the gas gap voltage

2019 ◽  
Vol 28 (2) ◽  
pp. 025002 ◽  
Author(s):  
Robert Bansemer ◽  
Ansgar Schmidt-Bleker ◽  
Ursula van Rienen ◽  
Klaus-Dieter Weltmann
Keyword(s):  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Dielectric Barrier ◽  
Gas Gap

scholarly journals Investigation of a Dielectric Barrier Discharge Plasma Actuator to Control Turbulent Boundary Layer Separation

2020 ◽  
Vol 10 (6) ◽  
pp. 1911 ◽  
Author(s):  
Mahdi Hasan ◽  
Michael Atkinson
Keyword(s):  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Three Dimensional ◽  
Flow Characteristics ◽  
Separated Flow ◽  
Boundary Layer Separation ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Dielectric Barrier ◽  
Baseline Case

A numerical investigation was carried out to explore the effects of a dielectric barrier discharge (DBD) plasma actuator on a three-dimensional incompressible, separated flow. The test article selected for the simulations was the National Aeronautical and Space Administration (NASA) wall-mounted hump model. The simulations were run at a Reynolds number of 936,000, based on hump chord length, and a freestream Mach number of 0.1. Hybrid partially averaged Navier–Stokes/large-eddy simulations (PANS/LES) were completed using CALC-LES, a well-validated computational fluid dynamics (CFD) code, developed by Chalmers University of Technology. The baseline code was modified to simulate the effects of the actuator, which were modeled as source terms in the momentum equation and were assumed to be steady and constant in the span-wise direction. The numerical simulations were carried out for a baseline (no control) case and five plasma control cases. To optimize the performance of the actuator, the variation of actuator location and voltage frequency was investigated. For the baseline case, a comparison of time-averaged skin friction, the coefficient of pressure, and velocity profiles was made of the available experimental results. The results of the baseline case showed good agreement for a hybrid turbulence model, thus strengthening the solver’s ability to predict a three-dimensional separated flow with reasonable accuracy. The results with the plasma actuator turned on showed improved flow characteristics compared to the baseline simulations by reducing the region of separated flow. The actuator placed just downstream of the separation point at an operational frequency of 5kHz completely eliminated the separated flow for our test conditions.

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