SparkJet Actuator Characterization in Supersonic Crossflow

Emerick, T.; Ali, Mohd Y.; Foster, Chase H.; Alvi, Farrukh S.; Popkin, Sarah Haack; Cybyk, Bohdan

doi:10.2514/6.2012-2814

Cited by 15 publications

(10 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The peck speed in certain parts of the jet flow reaches hundreds of meters per second by calculation and experiment. The experiments have been proved at supersonic speed wind tunnel tests [18][19][20]24] but few at low wind speed.…”

Section: Introductionmentioning

confidence: 99%

“…In the past decade, the spark discharge plasma synthetic jet has been researched by many academicians at such institutions as JHU/APL [12,[16][17][18], Florida A&M University [12,17,18], Florida State University [12,17,18], the University of Texas at Austin [19,20], Rutgers, the State University of New Jersey [21,22], NASA [22], the University of Illinois Urbana-Champaign [23,24], ONERA [25,26], the University of Ulsan [27], Nanjing University of Aeronautics and Astronautics [28,29], Air Force Engineering University China [30][31][32], and National University of Defense Technology [33,34]. The peck speed in certain parts of the jet flow reaches hundreds of meters per second by calculation and experiment.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets

Liu

Niu

Wang

et al. 2015

Sci. China Technol. Sci.

View full text Add to dashboard Cite

Spark discharge plasma synthetic jets (SPJs) have been used for the active flow control study on an NACA 0021 straight-wing model in a wind tunnel. The model forces and moments were measured using a six-component sting balance at a 20 m/s wind speed. The aim was to explore the SPJ's effect on airfoil aerodynamic by examining SPJ generators' position along the chordwise and the jet flow direction about the chord. Near the wing leading edge, two SPJ generators raised the stall angle by 2° and increased the maximum lift coefficient by 9%. The drag coefficient was decreased by 33.1%, and the lift-drag ratio was increased by 104.2% at an angle of attack above 16°. The rolling-moment coefficient was modified by 0.002, and the yawing-moment coefficient was changed by 0.0007 at angles of attack in the range of 0°-16°. The results showed that SPJs can control wing aerodynamic forces at a high angle of attack and moments at a low angle of attack. plasma synthetic jet, spark discharge, NACA 0021 airfoil, aerodynamic performance, aerodynamic control Citation: Liu R B, Niu Z G, Wang M M, et al. Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets.

show abstract

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Aerodynamic control of NACA 0021 airfoil model with spark discharge plasma synthetic jets

Liu

Niu

Wang

et al. 2015

Sci. China Technol. Sci.

View full text Add to dashboard Cite

show abstract

“…Toward characterization of the SparkJet in a high-speed flow application, the most recent SparkJet characterization efforts include wind-tunnel testing at FSU/FCAAP to examine flow interactions with a Mach 1.5 crossflow [25]. These test results demonstrated the ability of an array of SparkJets to influence the supersonic flowfield by generating an unsteady oblique shock.…”

Section: Sparkjet Operationmentioning

confidence: 99%

Experimental Estimation of SparkJet Efficiency

Popkin¹,

Cybyk²,

Foster³

et al. 2016

AIAA Journal

View full text Add to dashboard Cite

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

show abstract

“…Since the Johns Hopkins University Applied Physics Laboratory (JHU/APL) put forward a novel flow control actuator named plasma synthetic jet actuator (PSJA) or SparkJet actuator in 2003 [1], more and more investigations have been performed on this promising technology [2][3][4][5]. The research team in JHU has conducted a systematic study on the PSJA characteristics using Particle Image Velocimetry, schlieren system, dynamical pressure sensor and CFD method.…”

Section: Introductionmentioning

confidence: 99%