Seedless velocimetry at 100  kHz with picosecond-laser electronic-excitation tagging

Jiang, Naibo; Mance, Jason; Slipchenko, Mikhail N.; Felver, Josef; Stauffer, Hans U.; Yi, Tongxun; Danehy, Paul M.; Roy, Sukesh

doi:10.1364/ol.42.000239

Cited by 65 publications

(18 citation statements)

References 15 publications

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“…Its advantage over particle-based techniques in high-speed facilities is that it is not limited by timing issues associated with tracer injection (Haertig et al 2002) or reduced particle response at Knudsen and Reynolds numbers (Loth 2008) characteristic of high-speed wind tunnels. Methods of tagging velocimetry include the VENOM (Hsu et al 2009a,b;Sánchez-González et al 2011;Sánchez-González, Bowersox & North 2012, APART (Dam et al 2001;Sijtsema et al 2002;Van der Laan et al 2003), RELIEF (Miles et al 1987(Miles et al , 1989(Miles et al , 1993Miles & Lempert 1997;Miles et al 2000), FLEET (Michael et al 2011;Edwards, Dogariu & Miles 2015), STARFLEET (Jiang et al 2016), PLEET (Jiang et al 2017), argon (Mills 2016), iodine (McDaniel, Hiller & Hanson 1983;Balla 2013), sodium (Barker, Bishop & Rubinsztein-Dunlop 1997), acetone (Lempert et al 2002(Lempert et al , 2003Handa et al 2014), NH (Zhang et al 2017) and the hydroxyl group techniques, (Boedeker 1989;Wehrmeyer et al 1999;Pitz et al 2005;André et al 2017) among others (Hiller et al 1984;Gendrich & Koochesfahani 1996;Gendrich, Koochesfahani & Nocera 1997;Ribarov et al 1999;Stier & Koochesfahani 1999;André et al 2018).…”

Section: Diagnostic Approach: Tagging Velocimetrymentioning

confidence: 99%

Amplification and structure of streamwise-velocity fluctuations in compression-corner shock-wave/turbulent boundary-layer interactions

Mustafa

Parziale

Smith³

et al. 2019

J. Fluid Mech.

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In this work, we study the effect of the compression-corner angle on the streamwise turbulent kinetic energy (sTKE) and structure in Mach 2.8 flow. Krypton tagging velocimetry (KTV) is used to investigate the incoming turbulent boundary layer and flow over $8^{\circ }$, $16^{\circ }$, $24^{\circ }$ and $32^{\circ }$ compression corners. The experiments were performed in a 99 % $\text{N}_{2}$ and 1 % Kr gas mixture in the Arnold Engineering Development Complex (AEDC) Mach 3 Calibration Tunnel (M3CT) at $Re_{\unicode[STIX]{x1D6E9}}=1750$. A figure of merit is defined as the wall-normal integrated sTKE ($\overline{\text{sTKE}}$), which is designed to identify turbulence amplification by accounting for the root-mean-squared (r.m.s.) velocity fluctuations and shear-layer width for the different geometries. We observe that the $\overline{\text{sTKE}}$ increases as an exponential with the compression-corner angle near the root when normalized by the boundary-layer value. Additionally, snapshot proper orthogonal decomposition (POD) is applied to the KTV results to investigate the structure of the flow. From the POD results, we extract the dominant flow structures and compare each case by presenting mean-velocity maps that correspond to the largest positive and negative POD mode coefficients. Finally, the POD spectrum reveals an inertial range common to the boundary-layer and each compression-corner flow that is present after the first ${\approx}10$ dominant POD modes.

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Section: Diagnostic Approach: Tagging Velocimetrymentioning

confidence: 99%

Amplification and structure of streamwise-velocity fluctuations in compression-corner shock-wave/turbulent boundary-layer interactions

Mustafa

Parziale

Smith³

et al. 2019

J. Fluid Mech.

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“…Its advantage over PIV techniques in high-speed facilities is that it is not limited by timing issues associated with tracer injection [12] or reduced particle response at Knudsen and Reynolds numbers [4] characteristic of high-speed wind tunnels. Methods of tagging velocimetry include the VENOM [13][14][15][16][17], APART [18][19][20], RELIEF [21][22][23][24][25], FLEET [26,27], STARFLEET [28], PLEET [29], NO [30][31][32][33][34], argon [35], iodine [36,37], sodium [38], acetone [39][40][41], NH [42], and the hydroxyl group techniques [43][44][45][46], among others [47][48][49][50][51][52].…”

Section: Introductionmentioning

confidence: 99%

Single-Laser Krypton Tagging Velocimetry Investigation of Supersonic Air and N2 Boundary-Layer Flows over a Hollow Cylinder in a Shock Tube

2019

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In this paper, we investigate the boundary-layer profiles that form over a sharp, hollow cylinder in supersonic air and N 2 flows with a krypton tagging velocimetry (KTV) single-laser scheme. The supersonic flows are generated by the passage of the primary shock wave over the model in the Stevens shock tube. The experiments are performed in two gas mixtures doped with Kr: 99% N 2 /1% Kr, to model N 2 , and 75% N 2 /20% O 2 /5% Kr, to model air. The experimental setup allows us to vary the pressure and Reynolds number from 3-25 kPa and 1.5 × 10 5 to 1.5 × 10 6 m −1 , respectively, while the Mach number is kept fixed at 1.7. The static temperature and pressure (but not the velocity) are representative of typical large-scale high-enthalpy hypersonic impulse facilities. The KTV data points over the hollow cylinder are mapped to corresponding wall-normal locations above a flat plate, which enables comparison with the similarity solution for compressible boundary-layer flow. Agreement between the similarity solution and experimental results is excellent. Relative to previous two-laser KTV schemes, the single-laser approach used in this work has the advantage of being simpler and more cost effective, but it has a higher laserenergy requirement, 10 mJ/pulse in these experiments. Single-laser KTV is implemented by increasing the energy of the write-laser pulse to a sufficient level such that the Kr becomes partially ionized via a (2 + 1) resonance-enhanced, multiphoton ionization (REMPI) process with an excitation wavelength of 212.6 nm. The write step records the fluorescence that results primarily from the spontaneous emission from the two-photon excitation. After a prescribed delay, the read step records the fluorescence that results from the transitions that follow the recombination process. The signal-to-noise ratio (SNR) is sufficient to extract velocity profiles from single-shot, shock-tube experiments. Two-photon absorption cross-section calculations and emission spectra are presented to justify the chosen excitation wavelength and support our understanding of the Kr excitation and emission scheme.

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“…Its advantage over PIV techniques in high-speed facilities is that it is not limited by timing issues associated with tracer injection 12 or reduced particle response at Knudsen and Reynolds numbers 4 characteristic of high-speed wind tunnels. Methods of tagging velocimetry include the VENOM, [13][14][15][16][17] APART, [18][19][20] RELIEF, [21][22][23][24][25] FLEET, 26,27 STARFLEET, 28 PLEET, 29 argon, 30 iodine, 31,32 sodium, 33 acetone, [34][35][36] and the hydroxyl group techniques, [38][39][40] among others. [41][42][43][44][45] In this work, we use Krypton Tagging Velocimetry (KTV).…”

Section: Introductionmentioning

confidence: 99%

Two-Dimensional Krypton Tagging Velocimetry (KTV-2D) Investigation of Shock-Wave/Turbulent Boundary-Layer Interaction

Mustafa

Parziale

Marineau

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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Preliminary results from a two-dimensional Krypton Tagging Velocimetry (KTV-2D) investigation of a Mach 2.75 turbulent boundary and 24 degree compression corner flow are presented in this paper. KTV-2D is performed by creating a grid of tagged Kr atoms formed by intersecting laser lines and imaging the resulting fluorescence at a write step; then, after a time delay, imaging the translation of the grid by re-exciting the tagged atoms for the read step. The measurements were made in a 99% N2 and 1% Kr gas mixture. Spatial correlation was used to extract the velocity from the data. It was found that the streamwise component of the velocity in the boundary layer agrees well with the literature; however, a consistent bias was noted in the wall-normal velocity component in the boundary-layer and compression corner flows and we provide an explanation and correction for this bias which will easily be eliminated in future experimentation (the bias was a result of procedure, not inherent in the technique). The turning angle in the compression corner flow matches the result from classical inviscid theory, bringing confidence to the results.

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Seedless velocimetry at 100 kHz with picosecond-laser electronic-excitation tagging

Cited by 65 publications

References 15 publications

Amplification and structure of streamwise-velocity fluctuations in compression-corner shock-wave/turbulent boundary-layer interactions

Amplification and structure of streamwise-velocity fluctuations in compression-corner shock-wave/turbulent boundary-layer interactions

Single-Laser Krypton Tagging Velocimetry Investigation of Supersonic Air and N2 Boundary-Layer Flows over a Hollow Cylinder in a Shock Tube

Two-Dimensional Krypton Tagging Velocimetry (KTV-2D) Investigation of Shock-Wave/Turbulent Boundary-Layer Interaction

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