Experimental base flow modification on a swept wing using plasma forcing

Peng, Kaisheng; Arkesteijn, Joerie; Avallone, Francesco; Kotsonis, Marios

doi:10.1063/5.0118861

Cited by 5 publications

(2 citation statements)

References 43 publications

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“…Reconciling previous studies of Yadala et al, 24 Serpieri et al, 8 and Peng et al 41 as well as the current experiment, the stochastic PAinduced disturbances at both low and high frequencies can potentially damage the PA effectiveness for transition delay, at least within the context of BFM. For instance, to achieve the BFM control, the PA generally requires high power input and needs to be positioned close to the leading edge in order to favorably manipulate the CF component.…”

Section: B a Comment On Bfm Efficacysupporting

confidence: 87%

“…The overall transition advancement reported in the present study further highlights the detrimental effects of PA-induced unsteady disturbances and partially resolves the conundrum regarding the effects of unsteady forcing within the context of the BFM method. In the work of Peng et al, 41 the BFM-based PA was found to essentially impose two effects into the boundary layer. One is to weaken stationary CF instabilities (i.e., the intended BFM action), while the other is to enhance unsteady instabilities.…”

Section: Pa Effect On Transition Topology and Locationmentioning

confidence: 99%

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Unsteady disturbances in a swept wing boundary layer due to plasma forcing

2022

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This work investigates the response of a transitional boundary layer to spanwise-invariant dielectric barrier discharge plasma actuator (PA) forcing on a [Formula: see text] swept wing at a chord Reynolds number of [Formula: see text]. Two important parameters of the PA operation are scrutinized, namely, the forcing frequency and the streamwise location of forcing. An array of passive discrete roughness elements is installed near the leading edge to promote and condition a set of critical stationary crossflow (CF) instability modes. Numerical solutions of the boundary layer equations and linear stability theory are used in combination with the experimental pressure distribution to provide predictions of critical stationary and traveling CF instabilities. The laminar–turbulent transition front is visualized and quantified by means of infrared thermography. Measurements of velocity fields are performed using hotwire anemometry scans at specific chordwise locations. The results demonstrate the inherent introduction of unsteady velocity disturbances by the plasma forcing. It is shown that, depending on actuator frequency and location, these disturbances can evolve into typical CF instabilities. Positive traveling low-frequency type III modes are generally amplified by PA in all tested cases, while the occurrence of negative traveling high-frequency type I secondary modes is favored when PA is operating at high frequency and at relatively downstream locations, with respect to the leading edge.

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Section: B a Comment On Bfm Efficacysupporting

confidence: 87%

Section: Pa Effect On Transition Topology and Locationmentioning

confidence: 99%

Unsteady disturbances in a swept wing boundary layer due to plasma forcing

2022

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Effects of freestream turbulence on the secondary instability of the roughness-induced crossflow vortex in swept flat plate boundary layers

Nakagawa

Ishida

Tsukahara

2023

International Journal of Heat and Fluid Flow

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Plasma-based base flow modification on swept-wing boundary layers: dependence on flow parameters

Peng,

Avallone,

Kotsonis

2024

J. Fluid Mech.

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This work examines the control of cross-flow instabilities (CFIs) and laminar–turbulent transition on a swept wing, through the plasma-based base flow modification (BFM) technique. The effect of experimentally derived plasma body forces on the steady boundary layer base flow is explored through numerical simulations. Linear stability theory is subsequently used to predict the net BFM effect on CFIs. Based on these preliminary predictions, experiments are conducted in a low-turbulence wind tunnel where a spanwise-invariant plasma actuator is installed near the wing leading edge and operated at constant input voltage and frequency. Various flow parameters governing the plasma-based BFM technique are investigated, namely the Reynolds number, angle of attack and wavelength of excited stationary CFI modes. Stationary and travelling CFIs are quantified by planar particle image velocimetry while the transition topology and location are recorded by infrared thermography. The results confirm the stabilising effect of BFM on the swept-wing boundary layer. However, the plasma-based BFM is found to render the boundary layer more susceptible to travelling CFIs. In the presence of both net BFM effect and intrinsic plasma unsteady perturbations, the plasma-based BFM technique achieves transition delay with specific combinations of Reynolds number, angle of attack and wavelength of excited stationary CFI modes. The present findings provide insights into the fundamental principles of operating plasma actuators within the context of BFM control.

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Experimental base flow modification on a swept wing using plasma forcing

Cited by 5 publications

References 43 publications

Unsteady disturbances in a swept wing boundary layer due to plasma forcing

Unsteady disturbances in a swept wing boundary layer due to plasma forcing

Effects of freestream turbulence on the secondary instability of the roughness-induced crossflow vortex in swept flat plate boundary layers

Plasma-based base flow modification on swept-wing boundary layers: dependence on flow parameters

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