Characterization of Tollmien-Schlichting Wave Damping by DBD Plasma Actuators Using Phase-Locked PIV

Duchmann, Alexander; Kurz, Armin; Widmann, Alexander; Grundmann, Sven; Tropea, Cameron

doi:10.2514/6.2012-903

Cited by 24 publications

(6 citation statements)

References 6 publications

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“…Additional numerical and/or experimental work should be performed in order validate the present calculations or the similar flow conditions examined experimentally by Tropea and his co-workers. 7,8,10,11 Work of this manner may helpful in identifying exactly what sub-domain of the flow require bi-global stability analysis and which domains local stability analysis is sufficiently accurate. In addition to the presently examined two dimensional TS wave, evaluating the control authority of plasma actuation with respect to the most amplified perturbations 24 would be of significant importance.…”

Section: Discussionmentioning

confidence: 99%

Local and Bi-Global Stability Analysis of a Plasma Actuated Boundary Layer

Riherd

Roy

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Local and bi-global stability methods have been employed to examine the effects of flow-wise oriented dielectric barrier discharge actuators on a laminar, zero pressure gradient boundary layer. Both methods indicate that the Tollmien-Schlichting wave is stabilized when plasma actuators are used to add momentum into the boundary layer. The general behavior of boundary layer stabilization is consistent with experimental results. In addition to examining the hydrodynamic stability properties explicitly, elementary flow characterization has also been performed. This flow characterization is performed in order to better understand the changes to flow stability implicitly through the changes to shape factor and boundary layer heights caused by the use of plasma actuation.

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Section: Discussionmentioning

confidence: 99%

Local and Bi-Global Stability Analysis of a Plasma Actuated Boundary Layer

Riherd

Roy

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…Several experimental works have evidenced the potential of plasma actuation for delaying transition and extending regions of laminar flow Tropea 2007, 2009;Seraudie, Vermeersch, and Arnal 2011;Duchmann et al 2012;Kurz et al 2012;Duchmann et al 2013). For flat-plate flows, Tropea (2007, 2009) and Duchmann et al (2012) have shown that both continuous and pulsed plasma actuators could delay transition in the presence of zero and adverse pressure gradients.…”

Section: Introductionmentioning

confidence: 97%

“…For flat-plate flows, Tropea (2007, 2009) and Duchmann et al (2012) have shown that both continuous and pulsed plasma actuators could delay transition in the presence of zero and adverse pressure gradients. This was done by cancelling artificially excited Tollmien-Schlichting waves.…”

Section: Introductionmentioning

confidence: 98%

Delay of finite-span excrescence-induced transition using plasma-based control

Rizzetta

Visbal

2015

International Journal of Computational Fluid Dynamics

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Direct numerical simulations are carried out to explore the use of flow control that delays transition generated by excrescence on a plate-like geometry in subsonic flow. Both forward-facing and rearward-facing steps of small roughness heights are considered in the investigation. These are representative of joints and other surface imperfections on wing sections that disrupt laminar flow, thereby increasing skin friction and configuration drag. Unlike previous studies, the steps have a finite lateral extent, such that sharp edges occur in both the spanwise and streamwise directions, and provide a more realistic characterisation of misaligned panels in aerodynamic configurations. The effect of spanwise corners upon transition is examined, and dielectric barrier discharge plasma-based flow control is applied to delay transition and increase the extent of the laminar flow region. Solutions are obtained to the Navier-Stokes equations that were augmented by source terms used to represent body forces imparted by plasma actuators on the fluid. A simple phenomenological model provided these forces resulting from the electric field generated by the plasma. The numerical method is based upon a high-fidelity scheme and an implicit time-marching approach, on an overset mesh system that is used to represent the finite-span steps. Very small-amplitude numerical forcing is employed to generate perturbations, which are amplified by the geometric disturbances and result in transition, similar to the physical situation. Both continuous and pulsed operations of actuators are considered, and the effectiveness of the control is quantified. Transition with the forward-facing step is considerably exacerbated by the presence of a spanwise edge. Plasma control is minimally effective, even with the use of multiple actuators and increased applied force. For the rearward-facing step, transition is substantially delayed by plasma control with small force application. NomenclatureA = actuator pulsing amplitude function Cd = time-mean integrated drag coefficient Cf = time-mean skin friction coefficient D c = plasma scale parameter e c = electron charge, 1.6 × 10 −19 coulomb E = non-dimensional electric field vector E = total specific energy E r = reference electric field magnitude E x , E y , E z = non-dimensional components of the electric field vector E ω = turbulent kinetic energy nondimensional frequency spectral amplitude F, G, H, = inviscid vector fluxesviscous vector fluxes h = dimensional plate thickness, 2.0 in (0.00508 m) J = Jacobian of the coordinate transformation k = dimensional excrescence step height, 0.04 in (0.001 m) * Corresponding author. Email: donald.rizzetta@us.af.mil K = turbulent kinetic energy, 0.5(u u + v v + w w ) K i = integrated turbulent kinetic energy, δ y s Kdy M = Mach number p = non-dimensional static pressure Pr = Prandtl number, 0.73, for air q c = non-dimensional charge density Q = vector of dependent variables Q i = components of the heat flux vector Re = reference Reynolds number,Reu k k/h Re δ * , Re θ ...

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“…Grundmann and Tropea showed that plasma actuators could be used to delay the onset of turbulence in a laminar boundary layer [4,5]. A number of studies followed by various researchers, and the focus for many of these studies remained on the Tollmien-Schlichting (TS) route to turbulence [4,[6][7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

Stabilization of boundary layer streaks by plasma actuators

Riherd¹,

Roy

2014

J. Phys. D: Appl. Phys.

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A flow's transition from laminar to turbulent leads to increased levels of skin friction. In recent years, dielectric barrier discharge actuators have been shown to be able to delay the onset of turbulence in boundary layers. While the laminar to turbulent transition process can be initiated by several different instability mechanisms, so far, only stabilization of the Tollmien-Schlichting path to transition has received significant attention, leaving the stabilization of other transition paths using these actuators less explored. To fill that void, a bi-global stability analysis is used here to examine the stabilization of boundary layer streaks in a laminar boundary layer. These streaks, which are important to both transient and bypass instability mechanisms, are damped by the addition of a flow-wise oriented plasma body force to the boundary layer. Depending on the magnitude of the plasma actuation, this damping can be up to 25% of the perturbation's kinetic energy. The damping mechanism appears to be due to highly localized effects in the immediate vicinity of the body force, and when examined using a linearized Reynolds-averaged Navier-Stokes energy balance, indicate negative production of the perturbation's kinetic energy. Parametric studies of the stabilization have also been performed, varying the magnitude of the plasma actuator's body force and the spanwise wavenumber of the actuation. Based on these parametric studies, the damping of the boundary layer streaks appears to be linear with respect to the total amount of body force applied to the flow.

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Characterization of Tollmien-Schlichting Wave Damping by DBD Plasma Actuators Using Phase-Locked PIV

Cited by 24 publications

References 6 publications

Local and Bi-Global Stability Analysis of a Plasma Actuated Boundary Layer

Local and Bi-Global Stability Analysis of a Plasma Actuated Boundary Layer

Delay of finite-span excrescence-induced transition using plasma-based control

Stabilization of boundary layer streaks by plasma actuators

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