In-Flight Transition Delay with DBD Plasma Actuators

Duchmann, Alexander; Simon, Bernhard; Magin, Philip; Tropea, Cameron; Grundmann, Sven

doi:10.2514/6.2013-900

Cited by 21 publications

(6 citation statements)

References 16 publications

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“…Successful in-flight transition delay employing a steadily operated single DBD actuator is reported by Duchmann et al, 11 including an estimate of the overall efficiency of the flow control application. Boundary-layer transition on the pressure side of a natural laminar flow (NLF) wing glove is controlled at a flight speed of U ¼ 38 m/s on a motorized glider, rendering the chord Reynolds number Re c ¼ 3 Â 10 6 .…”

Section: Saving Ratementioning

confidence: 87%

“…In the second part (Secs. III-V), the suggested guideline is applied to the experimental data of Kriegseis et al [7][8][9][10] and Duchmann et al, 11 where the consecutive evaluation steps of this guideline are discussed in more detail. For the sake of conciseness, the respective experimental procedures are not presented here in their entirety; only the most relevant details and important results are recapped as a starting point for the present discussions.…”

Section: Introductionmentioning

confidence: 99%

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On the classification of dielectric barrier discharge plasma actuators: A comprehensive performance evaluation study

Kriegseis

Duchmann

Tropea

et al. 2013

Journal of Applied Physics

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Section: Saving Ratementioning

confidence: 87%

Section: Introductionmentioning

confidence: 99%

On the classification of dielectric barrier discharge plasma actuators: A comprehensive performance evaluation study

Kriegseis

Duchmann

Tropea

et al. 2013

Journal of Applied Physics

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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%

“…Hot wire anemometry and stability analyses confirmed that transition was delayed when the actuator was operated. Flight experiments were carried out by Duchmann et al (2013), employing a plasma actuator on the pressure side of a laminar flow wing section test article. Microphone and hot-wire measurements quantified a measurable, but modest amount of transition delay (3% chord).…”

Section: Introductionmentioning

confidence: 99%

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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“…Their study employed low-velocity wind tunnel testing (between 7 and 15 m s −1 ) and local stability theory to show the transition delay of the flow. Flight tests using continuous plasma actuation [17] also demonstrated a transition delay of 3% of the chord length for a small aircraft (a G109b motorized glider) for a high Reynolds number flow (Re x = u∞x ν ≈ 1.15 × 10 6 ). This work aims to describe the response of a boundary layer flow modified by plasma actuation to incoming TS waves in terms of the relevant physical mechanisms as well as to quantify the growth and decay rates of perturbations over the length of the boundary layer.…”

Section: Introductionmentioning

confidence: 99%

Damping Tollmien–Schlichting waves in a boundary layer using plasma actuators

Riherd¹,

Roy

2013

J. Phys. D: Appl. Phys.

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The response of a zero pressure gradient boundary layer modified by flow-wise oriented momentum injection similar to that of a plasma actuator is calculated using a two-dimensional (bi-global) stability analysis. It is found that the addition of momentum into the boundary layer has a significant impact on Tollmien-Schlichting waves, which may be damped by up to two orders of magnitude. Changes to the exponential growth rate of the perturbations are also measured. These stabilizing effects are largely due to the momentum addition modifying the downstream boundary layer profiles, but localized stabilization effects are also noted. The relative stabilization of the TS wave appears to be a linear function with respect to the ratio of the plasma-induced wall jet velocity under quiescent conditions and the free-stream velocity for lower levels of plasma actuation (i.e. velocity ratios less than 0.1). For higher levels of plasma actuation, the relative stabilization of the TS wave appears to be exponential with respect to the total momentum addition to the boundary layer by the plasma actuator.

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In-Flight Transition Delay with DBD Plasma Actuators

Cited by 21 publications

References 16 publications

On the classification of dielectric barrier discharge plasma actuators: A comprehensive performance evaluation study

On the classification of dielectric barrier discharge plasma actuators: A comprehensive performance evaluation study

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

Damping Tollmien–Schlichting waves in a boundary layer using plasma actuators

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