Abstract
Nanosecond dielectric barrier discharge (NSDBD) plasma actuators is relatively
new means of flow control. It has several advantages compared to more conventional
means of flow control, such as small size, low weight, fast response time
and controllability. It has been demonstrated to be able to promote transition of
boundary layers and to postpone flow separation on aerodynamic surfaces. This
makes the NSDBD actuator a promising technology for many applications in
aerospace and wind energy industries.
This thesis presents a study of NSDBD actuator effects by numerical simulations.
For the purposes of simulations of fluiddynamic effects of the actuation,
complex plasma dynamic processes are modeled by their thermal effects. This
is possible due to a large separation of scales between plasmadynamic, thermodynamic
and fluid dynamic phenomena. The resulting model is embedded into
the compressible computational fluid dynamics (CFD) simulation using Navier
Stokes equations. This model is then used in numerical simulations in two model
flows: a laminar boundary and a free shear layer. These model flows are relevant
for promotion of laminar to turbulent boundary layer transition and laminar
leading edge separation elimination.
For the laminar boundary case, the effect of a burst of discharges on a flat
plate boundary layer is studied. The shape, wavelength and propagation speed of
the disturbance introduced into the boundary layer by actuation are compared to
experimental results and found to be in agreement. This indicates that the thermal
model is adequate at predicting phenomenological effects of the actuation in this
case. POD analysis of the CFD flow fields is employed to identify the dominating
modes of the disturbance. The dominating mode is found to be the same as
the least stable mode predicted by linear stability theory. A compression wave,
however, is not found to play an important role, and the burst of pulses is found
to produce the same effects as the long pulse with the same total energy.
For the free shear layer case, the model of the actuator is placed on a centerline
in the beginning of a free shear layer. As a result of constant frequency actuation,
early formation of vortices and shear layer breakdown are observed. Each actuation event produces a convective disturbance in the flow field. Dynamics of the
disturbances are analyzed and growth rates are found to be in agreement with the
predictions of linear stability theory. A parametric study is carried out to study
scalability of the actuator effects to change of actuation frequency and energy per
pulse. A saturation effect with the increase of actuation frequency is observed.
For both studied cases, the effect of NSDBD actuation is excitation of natural
instability modes, which then evolve according to the stability properties of the
flow.
new means of flow control. It has several advantages compared to more conventional
means of flow control, such as small size, low weight, fast response time
and controllability. It has been demonstrated to be able to promote transition of
boundary layers and to postpone flow separation on aerodynamic surfaces. This
makes the NSDBD actuator a promising technology for many applications in
aerospace and wind energy industries.
This thesis presents a study of NSDBD actuator effects by numerical simulations.
For the purposes of simulations of fluiddynamic effects of the actuation,
complex plasma dynamic processes are modeled by their thermal effects. This
is possible due to a large separation of scales between plasmadynamic, thermodynamic
and fluid dynamic phenomena. The resulting model is embedded into
the compressible computational fluid dynamics (CFD) simulation using Navier
Stokes equations. This model is then used in numerical simulations in two model
flows: a laminar boundary and a free shear layer. These model flows are relevant
for promotion of laminar to turbulent boundary layer transition and laminar
leading edge separation elimination.
For the laminar boundary case, the effect of a burst of discharges on a flat
plate boundary layer is studied. The shape, wavelength and propagation speed of
the disturbance introduced into the boundary layer by actuation are compared to
experimental results and found to be in agreement. This indicates that the thermal
model is adequate at predicting phenomenological effects of the actuation in this
case. POD analysis of the CFD flow fields is employed to identify the dominating
modes of the disturbance. The dominating mode is found to be the same as
the least stable mode predicted by linear stability theory. A compression wave,
however, is not found to play an important role, and the burst of pulses is found
to produce the same effects as the long pulse with the same total energy.
For the free shear layer case, the model of the actuator is placed on a centerline
in the beginning of a free shear layer. As a result of constant frequency actuation,
early formation of vortices and shear layer breakdown are observed. Each actuation event produces a convective disturbance in the flow field. Dynamics of the
disturbances are analyzed and growth rates are found to be in agreement with the
predictions of linear stability theory. A parametric study is carried out to study
scalability of the actuator effects to change of actuation frequency and energy per
pulse. A saturation effect with the increase of actuation frequency is observed.
For both studied cases, the effect of NSDBD actuation is excitation of natural
instability modes, which then evolve according to the stability properties of the
flow.
Original language  English 

Qualification  Doctor of Philosophy 
Awarding Institution 

Supervisors/Advisors 

Award date  22 Mar 2016 
Print ISBNs  ISBN 9789461866172 
DOIs  
Publication status  Published  22 Mar 2016 
Keywords
 flow control
 plasma
 transition
 flow separation
 plasma actuators
 DBD
 NSDBD