Control of turbulent channel flow using a plasma-based body force

Li, Zexiang; Hu, Baopeng; Lan, Shilong; Zhang, Jinbai; Huang, Juan

doi:10.1016/j.compfluid.2015.07.001

Cited by 16 publications

(8 citation statements)

References 35 publications

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“…where 𝜌 𝑐 is the charge density and 𝐸 ⃗⃗ is the electric field. The simplified models include the Orlov model [45], Shyy model [20], and Suzen & Huang model [46,47]; these can significantly reduce the calculation times, especially for complex scenarios or 3D geometries, such as boundary-layer separation control, turbine blades, and channel flow [48][49][50][51]. Considering relative permittivity properties of the working fluid and actuator materials, the simplified DBD models define the charge density as a one-dimensional boundary condition with a half Gaussian distribution starting at the edge of the ground electrode closest to the active electrode [44].…”

Section: Introductionmentioning

confidence: 99%

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Tang¹,

Vaddi²,

Mamishev³

et al. 2021

J. Phys. D: Appl. Phys.

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Dielectric barrier discharge (DBD) plasma actuators with an asymmetric, straight edge electrode configuration generate a wall-bounded jet without moving parts. Mechanistic description of the interaction between the Coulombic forces and fluid motion as a function of DBD parameters remains unclear. This paper presents an experimental investigation of DBD actuators, including electrical current associated with microdischarges, plasma volume and the wall jet momentum over a range of alternating current (AC) frequencies (0.5–2 kHz) and peak-to-peak voltages up to 19.5 kV. Discharge current is measured with a high temporal resolution, plasma volume is characterized optically and the momentum induced by the DBD wall jet is computed based on the axial velocities measured downstream of the actuator using a custom-built pitot tube. Discharge current analysis demonstrated asymmetry between the positive and negative semi-cycle; both currents yielded a power–law relationship with empirical fitting coefficients. Plasma length varies linearly and volume quadratically with voltage. Although plasma length reached an asymptotic value at a higher frequency, the plasma volume grows due to the increasing height of the ionization region. In a simple two-dimensional configuration, the DBD wall jet momentum shows near-linear dependency with discharge current in the range of voltages and frequencies considered in this work. The presented empirical model characterizes the DBD wall jet momentum and the discharge current based only on the AC inputs. With the estimation of plasma volume, the model can be applied for determining more realistic boundary conditions in numerical simulations.

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Section: Introductionmentioning

confidence: 99%

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Tang¹,

Vaddi²,

Mamishev³

et al. 2021

J. Phys. D: Appl. Phys.

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show abstract

“…The most popular of those models are the Orlov model (14), the Shyy model (15) and the Suzen & Huang model (1,2) because of their relative simplicity and ability to mimic the time-averaged effects of a DBD actuator on the ambient fluid. Those three models have been tested in various flow configurations: boundary-layer separation control for the Orlov model (14), turbine blades (1,2), channel flow (16) and tandem of cylinders (17) for the Suzen & Huang model and channel flow (18) and transition control around an airfoil (19) for the Shyy model. These models have two major drawbacks.…”

Section: Introductionmentioning

confidence: 99%

Modelling of Dielectric Barrier Discharge Plasma Actuators for Direct Numerical Simulations

Brauner

Laizet

Bénard

et al. 2016

8th AIAA Flow Control Conference

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In recent years the development of devices known as plasma actuators has advanced the promise of controlling flows in new ways that increase lift, reduce drag and improve aerodynamic efficiencies; advances that may lead to safer, more efficient and quieter aircraft. The large number of parameters (location of the actuator, orientation, size, relative placement of the embedded and exposed electrodes, materials, applied voltage, frequency) affecting the performance of plasma actuators makes their development, testing and optimisation a very complicated task. Several approaches have been proposed for developing numerical models for plasma actuators. The discharge can be modelled by physics-based kinetic methods based on first principles, by semi-empirical phenomenological approaches and by PIV-based methods where the discharge is replaced by a steady-state body force. The latter approach receives a recent interest for its easy implementation in RANS and U-RANS solvers. Here, a forcing term extracted from experiments is implemented into our high-order Navier-Stokes solver (DNS) in order to evaluate its robustness and ability to mimic the effects of a surface dielectric barrier discharge. This experimental forcing term is compared to the numerical forcing term developed by Suzen & Huang (1, 2) with an emphasis on the importance of the wall-normal component of each model.

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“…A computational study, by DNS, of a controlled turbulent channel flow by two plasma actuators (located on both upper and lower wall) is presented by Li et al 128 Two changes in the behavior of skin-friction coefficient are observed. Over the forcing region, there is a large increase in the skin-friction coefficient due to the change in the velocity gradient.…”

Section: Active Flow Controlmentioning

confidence: 99%

Current state and future trends in boundary layer control on lifting surfaces

Svorcan

Wang

Griffin

2022

Advances in Mechanical Engineering

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Successful flow control may bring numerous benefits, such as flow stabilization, flow reattachment, separation delay, drag reduction, lift increase, aerodynamic performance improvement, energy efficiency increase, shock delay or weakening, noise reduction, etc. For these purposes, many different flow control devices, which can be classified as passive, semi-active and active, have been designed and tested. This review paper aims to highlight the most promising and commonly employed boundary layer control methods as well as outline their potential in specific applications in aerospace and energy engineering. Referenced studies, performed on various geometries (flat plates, channels, airfoils, wings, blades, cylinders), are primarily numerical or experimental. Although enhanced aerodynamic performance is achieved in many cases, further research is required to draw general conclusions. This paper aims to demonstrate that, in the future, we may expect further developments of flow control actuators, as well as their increased application.

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Control of turbulent channel flow using a plasma-based body force

Cited by 16 publications

References 35 publications

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Modelling of Dielectric Barrier Discharge Plasma Actuators for Direct Numerical Simulations

Current state and future trends in boundary layer control on lifting surfaces

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