High-Speed and High-Reynolds-Number Jet Control Using Localized Arc Filament Plasma Actuators

Samimy, Mo; Kearney-Fischer, Martin; Kim, J.-H.; Sinha, Aniruddha

doi:10.2514/1.b34272

Cited by 102 publications

(42 citation statements)

References 80 publications

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“…Current programs directed at jet noise reduction are demonstrating benefits of several decibels using passive and active control methods to increase jet mixing and break up shock cells in the over-expanded flow (e.g. Alkislar, Krothapalli & Butler 2007;Henderson 2010;Samimy et al 2012). † Email address for correspondence: sinha.aniruddha@gmail.com Noise reduction through novel nozzle designs and active/passive flow control requires a large number of cost-function (far-field noise) evaluations in the process of optimization and control strategy identification.…”

Section: Introductionmentioning

confidence: 99%

Wavepacket models for supersonic jet noise

et al. 2014

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Gudmundsson and Colonius (J. Fluid Mech., vol. 689, 2011, pp. 97-128) have recently shown that the average evolution of low-frequency, low-azimuthal modal large-scale structures in the near field of subsonic jets are remarkably well predicted as linear instability waves of the turbulent mean flow using parabolized stability equations. In this work, we extend this modelling technique to an isothermal and a moderately heated Mach 1.5 jet for which the mean flow fields are obtained from a high-fidelity large-eddy simulation database. The latter affords a rigourous and extensive validation of the model, which had only been pursued earlier with more limited experimental data. A filter based on proper orthogonal decomposition is applied to the data to extract the most energetic coherent components. These components display a distinct wavepacket character, and agree fairly well with the parabolized stability equations model predictions in terms of near-field pressure and flow velocity. We next apply a Kirchhoff surface acoustic propagation technique to the near-field pressure model and obtain an encouraging match for far-field noise levels in the peak aft direction. The results suggest that linear wavepackets in the turbulence are responsible for the loudest portion of the supersonic jet acoustic field.

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Section: Introductionmentioning

confidence: 99%

Wavepacket models for supersonic jet noise

et al. 2014

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“…2 The LAFPAs have thereby been proven effective for both mixing enhancement and noise reduction over a large range of Mach numbers and temperatures (see Ref. 10 for a recent review).…”

Section: Introductionmentioning

confidence: 99%

The impulse response of a high-speed jet forced with localized arc filament plasma actuators

et al. 2012

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Experimental study of planar opposed jets with acoustic excitation Phys. Fluids 25, 014108 (2013) Similarity analysis of the momentum field of a subsonic, plane air jet with varying jet-exit and local Reynolds numbers Phys. Fluids 25, 015115 (2013) Electrohydrodynamic printing under applied pole-type nozzle configuration Appl. Phys. Lett. 102, 024101 (2013) Effects of fluid properties and laser fluence on jet formation during laser direct writing of glycerol solution J. Appl. Phys. 112, 083105 (2012) We present experimental and theoretical analyses of the response of high-speed, highReynolds-number, round jets to impulsive forcing with arc-filament-plasma actuators. The impulse response is obtained with forcing Strouhal numbers, based on the nozzle exit diameter and exit center line velocity, less than 0.1. The resulting phase-averaged near-field pressure signature displays a compact wave with a positive peak preceding a negative one, indicative of a large scale structure in the shear layer of the jet. Scaling laws derived by operating the jet at four subsonic Mach numbers are used to distinguish this hydrodynamic component of the phase-averaged jet response from the direct actuator noise. As the forcing frequency increases, the compact waves in the near-field pressure signal overlap each other, indicating interaction of the growing seeded structures. For this regime, the phase-averaged response is approximately replicated by linear superposition of the impulse response, thereby demonstrating the quasi-linearity of structure interaction. A novel application of linear parabolized stability theory yields a successful model of the impulse response. C 2012 American Institute of Physics. [http://dx

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“…LAFPAs operate by introducing heat using an arc discharge very near the flow surface, which produces an unsteady influence on the flow. These actuators exhibit a very wide bandwidth and, for some applications, have sufficient amplitude to affect flows at low supersonic speeds [12]. With the goal of developing an actuator capable of high-frequency actuation and high-momentum throughput over a large range of frequencies and with phasing capabilities, the Johns Hopkins University Applied Physics Laboratory (JHU/APL), in collaboration with Florida State University/Florida Center for Advanced Aero-Propulsion (FSU/FCAAP), has been investigating the JHU/APL-invented [13] SparkJet actuator.…”

Section: Introductionmentioning

confidence: 99%

Experimental Estimation of SparkJet Efficiency

Popkin¹,

Cybyk²,

Foster³

et al. 2016

AIAA Journal

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The results presented herein include SparkJet characterization studies with a focus on understanding the actuator efficiency during stage 1 and the resulting flowfield. Experimental cavity pressure and arc power measurements are used to estimate efficiency whereas experimental microschlieren images are used to visualize the flowfield and quantify the velocity of distinct flow features. The experimental measurements used to estimate efficiency during stage 1 of a single SparkJet cycle were acquired using a single orifice SparkJet design in a quiescent environment. The experiments evaluated efficiency as a function of cavity volume (42.4-169.6 mm 3 ), orifice diameter (0.4-2.0 mm), and input energy (0.17-0.77 J per pulse). The results show that efficiency is a function of parasitic resistance in circuit components, high-temperature gas dynamics, and the ratio of input energy to internal energy of the cavity air, Q C ∕E. The circuit design used here was approximately 80% efficient and the pressure-based efficiency decreased from 40 to 20% as Q C ∕E increased from 5 to 60. Adjusting the pressure-based efficiency calculation to be a function of the measured arc energy, the conversion from arc energy to the energy available to raise the cavity pressure was 40-45% efficient. Using a SparkJet four-orifice array design (cavity volume of 363 mm 3 and each orifice 0.4 mm in diameter) in a quiescent environment, phase-averaged microschlieren images of a single SparkJet cycle reveal the rapid flow development when the first evidence of flow is seen 8 μs after the SparkJet initiation and a well-developed jet is visible by 100 μs. Also based on these calibrated images, the maximum jet velocity was estimated at 250 m∕s. Nomenclature C= capacitance, F C v = specific heat for a constant volume, J∕kg K E = internal energy, J I = current, A m = mass, kg n = frequency mode P = pressure, Pa Q = energy, J R = gas constant, J∕kg K T = temperature, K t = time, s U = jet velocity, m∕s V = voltage across capacitors, V γ = ratio of specific heats η = efficiency θ = molecular vibrational energy constant, K ρ = density, kg∕m 3 ω 0 = frequency, rad∕s Subscripts A = related to arc discharge C = related to capacitor P = related to pressure p = values corresponding to calorically perfect gas T = related to temperature 1 = conditions before arc 2 = conditions after arc

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High-Speed and High-Reynolds-Number Jet Control Using Localized Arc Filament Plasma Actuators

Cited by 102 publications

References 80 publications

Wavepacket models for supersonic jet noise

Wavepacket models for supersonic jet noise

The impulse response of a high-speed jet forced with localized arc filament plasma actuators

Experimental Estimation of SparkJet Efficiency

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