TY - JOUR
T1 - Numerical Technique for Implementation of SDBD Plasma Actuators for Flow Control Applications in Wing Surfaces
AU - Orozco, Raúl Bernal
AU - Huerta Chávez, Oliver Marcel
AU - Ortega Herrera, José Ángel
AU - Montaño, Alfredo Arias
N1 - Publisher Copyright:
© 2022 Instituto Politecnico Nacional. All rights reserved.
PY - 2022
Y1 - 2022
N2 - In the subsequent study a Computational Fluid Dynamics (CFD) analysis technique to simulate a plasma actuator over an airfoil Re = O(205) is presented. The technique uses a two-dimensional Reynolds-Averaged Navier-Stokes Method coupled to the Kloker plasma-fluid model to study the effects of a Single Dielectric-Barrier Discharge (SDBD) as a Plasma Actuator. The CFD technique have been implemented in OpenFOAM platform for two setups, when: i) the actuator was located at x/c = 0.03 and ii) x/c = 0.1 of the chord length of the airfoil. The magnitude of the body force is equivalent to the results obtained by Hofkens and the actuator operates for both cases in the continuous and in the burst mode. To perform the numerical technique for a stable solution in OpenFOAM, various numerical procedures were tested, including a mixed solver between PISO and SIMPLE algorithm better known as pimpleFoam with nCorrector. The cases were solved in parallel on distributed processors using OpenMPI implementation and the accuracy of the results are strongly depends on the choice of grid size, y-plus, wall function and discretization scheme. The results indicate a high potential, suitability and great capabilities of this numerical technique implemented in OpenFOAM platform for free instability flow simulation.
AB - In the subsequent study a Computational Fluid Dynamics (CFD) analysis technique to simulate a plasma actuator over an airfoil Re = O(205) is presented. The technique uses a two-dimensional Reynolds-Averaged Navier-Stokes Method coupled to the Kloker plasma-fluid model to study the effects of a Single Dielectric-Barrier Discharge (SDBD) as a Plasma Actuator. The CFD technique have been implemented in OpenFOAM platform for two setups, when: i) the actuator was located at x/c = 0.03 and ii) x/c = 0.1 of the chord length of the airfoil. The magnitude of the body force is equivalent to the results obtained by Hofkens and the actuator operates for both cases in the continuous and in the burst mode. To perform the numerical technique for a stable solution in OpenFOAM, various numerical procedures were tested, including a mixed solver between PISO and SIMPLE algorithm better known as pimpleFoam with nCorrector. The cases were solved in parallel on distributed processors using OpenMPI implementation and the accuracy of the results are strongly depends on the choice of grid size, y-plus, wall function and discretization scheme. The results indicate a high potential, suitability and great capabilities of this numerical technique implemented in OpenFOAM platform for free instability flow simulation.
KW - SDBD
KW - airfoil with plasma actuator
KW - flow separation control
KW - low reynolds
UR - http://www.scopus.com/inward/record.url?scp=85146984060&partnerID=8YFLogxK
U2 - 10.13053/CyS-26-4-3424
DO - 10.13053/CyS-26-4-3424
M3 - Artículo
AN - SCOPUS:85146984060
SN - 1405-5546
VL - 26
SP - 1527
EP - 1538
JO - Computacion y Sistemas
JF - Computacion y Sistemas
IS - 4
ER -